bepicolumbo mtm electric propulsion system (meps): solar...

BC.ASU.SP.00008

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Document Autogenerated from DOORS Module : /BepiColombo Implementation Phase/Level 3 Equipment Specifications/MPB/SEPS Specification BC_ASU_SP_00008_SEPS_Spec_Formal_Issue1 No_Names_09_08_07.doc

BepiColumbo MTM Electric Propulsion System (MEPS): Solar Electric Propulsion Subsystem (SEPS) Specification

CI CODE: B3138 DRL Refs : EN-016

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Prepared by: Date:

Checked by: Date:

Approved by: Date:

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This document is produced under ESA contract, ESA export exemptions may therefore apply. These Technologies may require an export licence if exported from the EU

© Astrium Limited 2007

Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any

purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.

Astrium Limited, Registered in England and Wales No. 2449259

Registered Office: Gunnels Wood Road, Stevenage, Hertfordshire, SG1 2AS, England

BC.ASU.SP.00008 Issue 01

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Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner.

BC_ASU_SP_00008_SEPS_Spec_Formal_Issue1 No_Names_09_08_07.doc

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CONTENTS 1 Introduction and Scope ............................................................................................................................. 6

1.1 Introduction ........................................................................................................................................ 6 1.2 Scope ................................................................................................................................................. 6 1.3 Summary Description......................................................................................................................... 6 1.4 MCU Background Information............................................................................................................ 6 1.5 Pipework and Harness ....................................................................................................................... 7

2 Documents ................................................................................................................................................ 9 2.1 Applicable Documents ....................................................................................................................... 9 2.2 Reference Documents ..................................................................................................................... 10 2.3 ECSS Standards ( Reference )........................................................................................................ 10

2.3.1 Space Engineering.................................................................................................................... 10 3 Subsystem and Unit Functional and Performance Requirements .......................................................... 11

3.1 SEPS Function................................................................................................................................. 11 3.2 Functional Requirements ................................................................................................................. 11

3.2.1 Operating Pressures ................................................................................................................. 11 3.2.2 Leakage .................................................................................................................................... 11 3.2.3 Propellant Specification ............................................................................................................ 11 3.2.4 FCU Configuration .................................................................................................................... 12 3.2.5 Redundancy.............................................................................................................................. 12 3.2.6 Thruster Neutralisers ................................................................................................................ 13 3.2.7 SEPS Operations and Modes................................................................................................... 13

3.3 Performance Requirements ............................................................................................................. 18 3.3.1 Thrust ........................................................................................................................................ 19 3.3.2 Specific Impulse........................................................................................................................ 19 3.3.3 Power Consumption.................................................................................................................. 20 3.3.4 Power Dissipation ..................................................................................................................... 20 3.3.5 Performance Models................................................................................................................. 21 3.3.6 Response Time......................................................................................................................... 21 3.3.7 Beam-Out Limits ....................................................................................................................... 21 3.3.8 Thrust Vector ............................................................................................................................ 21 3.3.9 Thruster Plume ......................................................................................................................... 22 3.3.10 SEPS Life.................................................................................................................................. 22

4 Subsystem and Unit Specific Design and Interface Requirements......................................................... 26 4.1 Design Criteria ................................................................................................................................. 26

4.1.1 Proof and Burst Pressures........................................................................................................ 26 4.1.2 Mechanical Design and Interface Requirements...................................................................... 26 4.1.3 Thermal Design and Interface Requirements........................................................................... 27 4.1.4 Electrical Requirements ............................................................................................................ 30 4.1.5 Design and Construction........................................................................................................... 32

4.2 Environmental Design Requirements .............................................................................................. 35 4.2.1 Pre-Launch (Including Spacecraft Level Tests, Storage and Transportation).......................... 35 4.2.2 Launch ...................................................................................................................................... 36 4.2.3 Cruise Phase Enviroment ......................................................................................................... 37

4.3 Physical Characteristics ................................................................................................................... 38 4.3.1 Configuration and Dimensions.................................................................................................. 38 4.3.2 Mass Properties ........................................................................................................................ 38 4.3.3 Stiffness Requirements............................................................................................................. 38 4.3.4 Interfaces .................................................................................................................................. 39

4.4 Miscellaneous .................................................................................................................................. 40 4.4.1 Accessibility / Maintainability .................................................................................................... 40 4.4.2 Transportation, Handling and Storage...................................................................................... 41

5 Product Assurance .................................................................................................................................. 42 5.1 Failure Tolerance ............................................................................................................................. 42

6 Verification and Test Requirements ........................................................................................................ 44 6.1 General requirements ...................................................................................................................... 44


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6.1.1 Responsibility for Inspection and Test ...................................................................................... 44 6.1.2 Quality Assurance Programme................................................................................................. 44 6.1.3 Surveillance, and Witness of Inspection and Test.................................................................... 44 6.1.4 Preproduction Sample .............................................................................................................. 44 6.1.5 Classification of Inspection and Test ........................................................................................ 44 6.1.6 Thruster Firing Tests................................................................................................................. 45

6.2 Verification of Compliance ............................................................................................................... 46 6.2.1 General ..................................................................................................................................... 46 6.2.2 Acceptance Inspection and Test............................................................................................... 46 6.2.3 Qualification Inspection and Test.............................................................................................. 48

6.3 Test Conditions and Test Equipment............................................................................................... 51 6.3.1 Ambient Conditions................................................................................................................... 51 6.3.2 Test Equipment......................................................................................................................... 52 6.3.3 Tolerance of Test Conditions (Excluding Ambient) .................................................................. 52 6.3.4 Accuracy of Measurement ........................................................................................................ 53 6.3.5 Test Media ................................................................................................................................ 53 6.3.6 Product Test Controls ............................................................................................................... 53

6.4 Test Methods ................................................................................................................................... 53 6.4.1 Inspection/Examination............................................................................................................. 53 6.4.2 Proof Pressure Test .................................................................................................................. 54 6.4.3 Leakage Tests .......................................................................................................................... 55 6.4.4 Burst Test.................................................................................................................................. 55 6.4.5 Functional Tests........................................................................................................................ 55 6.4.6 Performance Tests.................................................................................................................... 57 6.4.7 Vibration Tests .......................................................................................................................... 57 6.4.8 Constant Acceleration............................................................................................................... 59 6.4.9 Thermal Vacuum Tests............................................................................................................. 59 6.4.10 EMC Tests ................................................................................................................................ 60 6.4.11 Cleanliness Verification............................................................................................................. 60 6.4.12 Visual Inspection....................................................................................................................... 61 6.4.13 Preparation for Data Review..................................................................................................... 61 6.4.14 Shock Test ................................................................................................................................ 61

6.5 Preparation for Delivery, Inspection and Test.................................................................................. 62 6.6 Documentation ................................................................................................................................. 62

7 Abbreviations List .................................................................................................................................... 63 8 GDIR Applicability Matrix......................................................................................................................... 65 9 EMC Applicability Matrix......................................................................................................................... 96 10 Enviroment and Test Applicability Matrix.......................................................................................... 104 11 Operational and Autonomy Applicability Matrix ................................................................................. 111

FIGURES Figure 3.3-1: SEPS Specific Impulse Requirements..................................................................................... 19 Figure 3.3-2: SEPS Power Requirements..................................................................................................... 20


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1 INTRODUCTION AND SCOPE

1.1 Introduction

This document defines the requirements applicable for the Solar Electric Propulsion System (SEPS) to be used as part of the BepiColombo MTM Electric Propulsion System (MEPS).

BepiColombo is ESA’s cornerstone mission to Mercury to be launched in 2013.

1.2 Scope

This document comprises the technical requirements and constraints for the BepiColombo SEPS; these requirements are for both SEPS level, and also for the equipments which go to make up the SEPS as defined in Section 1.3 below. This includes:

• The performance, design and interface requirements of subject hardware

• The testing and verification requirements

All other elements of the BepiColombo MEPS (feed system, pointing mechanisms, etc.), as well as higher level activities are considered to be outside the scope of this specification

1.3 Summary Description

The SEPS comprises the following items:

• 4 ion thrusters (SEPT), including neutralisers

• 4 flow control units (FCU, 1 per thruster)

• Power processing units (PPU)1,2

• All pipework and harnesses interconnecting the SEPTs, FCUs and PPUs3

Note 1: The power processing units shall contain all the necessary electronics, and be of sufficient quantity, power rating and switching capability, to enable any of the following thruster operations (each thruster being capable of operating within the performance range identified in the SEPS specification):

• Single operation of any 1 of the 4 thrusters, and:

• Simultaneous operation of any 2 of the 4 thrusters

Note 2: If any of the above electronics are housed in units other than the PPUs, all command, control, telemetry and power still has to be routed via the PPUs. The SEPS Contractor shall identify any specific units which have to be provided for operation of their thruster system, which are housed separately from the main PPUs.

Note 3: Although the propellant feed system and any pointing mechanisms required are not considered part of the SEPS defined herein, it should also be noted that the pipework and harness to the thruster will require sufficient flexibility for the thruster to be moved on its pointing mechanism, with the FCU and PPU hard mounted to the spacecraft structure. This detailed further in Section 3.3.10.3 below.

All items of the Xenon gas feed system, and thruster pointing mechanisms, are NOT considered to be part of the SEPS as defined herein. However, in the event that any of these equipments introduces a significant coupling with the SEPS (e.g. functionally, mechanically or thermally), representative units may be made available by the Customer for the relevant necessary verification activities.

A thruster function chain is defined as a thruster, its associated FCU, any electronics which is dedicated to that thruster, and all interconnecting harness and pipework.

The thruster control functions (hardware and software/Firmware) are to be provided from within the SEPS.

1.4 MCU Background Information

The command and data handling from the spacecraft to the SEPS is all routed through the MEPS control unit (MCU). (This unit also provides functions related to management and control of the TPAs and HPR).

The MCU functional requirements, related to SEPS operations, can be summarised as follows:


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• Reception of TC from, and sending of TM to the spacecraft AOCS (via the spacecraft MIL-STD-1553B bus)

• Sending TC to and reception of TM from the SEPS PPUs (via a separate dedicated MIL-STD-1553B data bus)

• Management of MEPS (including SEPS) configuration selection and mode transitions under spacecraft command

• MEPS FDIR; places system into safe state and sends error reports back to spacecraft in case of any failure (reconfigurations have to be done by the spacecraft as these require reconfiguration of AOCS, power system, etc.)

• TM buffering

The MCU also is responsible for pressure regulation closed loop control and thruster pointing closed loop control (sending discrete commands to and reception of discrete TM from the HPR and TPA), and the management of SEPS, pressure regulation and thruster pointing function interactions

The MCU is a Packet terminal and includes software updatable in flight. The MCU is responsible for providing the AOCS, the on-board autonomy and ground with all relevant telemetry from the MEPS (including the SEPS TM) in packetised format. It is the single entry point for commands to the Electric Propulsion subsystem.

The only interfaces to the SEPS which are not routed through the MCU are high level ON/OFF commands (relay switching), and the main 100V power bus, both of which are provided direct from the PCDU.

1.5 Pipework and Harness

The overall approach for the SEPS pipework and harness responsibilities is as shown in Appendix K of BC-ASU-SW-00008.

The overall approach for the SEPS pipework and harness responsibilities is as follows:

• The SEPS supplier is the design authority for the pipework and harness between the PPU, FCU and thruster, including any radiation shielding required

• The routing definition for this pipework and harness is allocated to the TPA supplier, along with the mechanical and fatigue analysis, interference analysis, and support definition

• All pipework and harness hardware(including shielding) is provided by the SEPS supplier

• An initial confidence test is to be conducted by the TPA supplier using samples from the SEPS supplier, as discussed below; this is to be completed prior to the SEPS and TPA CDRs

• The SEPS supplier shall pre-form the qualification, STM, EM and flight pipework and harnesses in accordance with the routing defined by the TPA supplier, and verify their integrity

• The TPA supplier shall integrate the pipework and harnesses to the TPMs; in case of supports which are to be on the spacecraft, these shall be reproduced for TPM testing

• The TPA shall be subjected to its test programme with the above pipework and harness on place (including the fatigue life test for the qualification)

• Final verification of integrity will be perfomed by the SEPS supplier

• The TPMs shall be delivered to Astrium satellites with the pipework and harness attached


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2 DOCUMENTS

2.1 Applicable Documents

SEPS-10//R

The following documents of the latest issue shall be applicable to this specification.

In the event of conflict between this specification and any of the applicable documents referenced below, this conflict shall be notified to the Customer.

SEPS-992//R

AD Title Doc-No

AD 01 General Design and Interface Requirements (GDIR)

BC-ASD-SP-00001

AD 02 Environment Requirements and Test Specification

BC-ASD-SP-00002

AD 03 EMC/ESD Design and Test Requirements Specification

BC-ASD-SP-00033

AD 04

AD 05 Management Requirements for Subcontractors

BC-ASD-SP-00024

AD 06 Configuration & Data Management Requirements Specification

BC-ASD-SP-00006

AD 07 SW PA Requirements for Subcontractors

BC-ASD-SP-00009

AD 08 PA Requirements for Subcontractors

BC-ASD-SP-00018

AD 09 CSG Safety Regulations General Rules

CSG-RS-10A-CN, Vol.1

AD 10 CSG Safety Regulations Specific Rules

CSG-RS-21A-CN, Vol.2, Pt 1

AD 11 Helium MIL-PRF-27407B

AD 12 Nitrogen MIL-PRF-27401D

AD 13 Xenon GOST 10219-77

AD 14 Isopropyl Alcohol TT-I-735A(3)

AD 15 MIL-STD-1553B Bus Protocol Specification

BC-ASD-SP-00016

AD 16 Operational And Autonomy Requirement Specification

BC-ASD-SP-00044-OPA


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AD Title Doc-No

AD 17 Functional Simulation Model Input Guideline

BC-ASD-SP-00023

AD 18 Thermal Model Specification BC-ASD-SP-00030

AD 19

AD 20 Onboard Software Definition Document (OBSDD)

To be issued at a later date.

AD 21 S/C DB Specification BC-ASD-RS-00014

2.2 Reference Documents

RD 01 Micrometeroids Test Results Report

_

2.3 ECSS Standards ( Reference )

2.3.1 Space Engineering

RD04 E-30 Part 5.1A Mechanical - Part 5.1: Propulsion . Liquid and electric propulsion for spacecraft

RD05 E-30 Part 7A

Mechanical - Part 7: Mechanical parts

RD06 E-30 Part 8A

Mechanical - Part 8: Materials

RD07 E-30 Part 1A

Mechanical - Part 1: Thermal Control

RD08 E-40 Part 1B

Software - Part 1: Principles and requirements

RD10 E-70 Part 2A

Software - Part 2: Document requirements definitions (DRDs)


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3 SUBSYSTEM AND UNIT FUNCTIONAL AND PERFORMANCE REQUIREMENTS

3.1 SEPS Function

The SEPS shall provide sufficient thrust and impulse to fulfil the BepiColombo spacecraft transfer from Earth to Mercury, excluding Earth escape and Mercury capture; the corresponding SEPS requirements are specified in this document.

The SEPS shall be fed with high purity Xenon at a regulated pressure, and with the necessary electrical power from a nominal 100V regulated bus, as detailed in Section 4.3.4.1 and Section 4.1.4.3 below.

The SEPS shall fulfil these mission requirements both nominally and in the event of any single failure within the SEPS, as detailed in Section 3.2.5 below.

3.2 Functional Requirements

3.2.1 Operating Pressures

All pressures in this document are absolute, unless otherwise stated

SEPS-16//T

The FCU inlet maximum expected pressure (MEP) is 10 bar (non-operational). The FCU valves shall be capable of operation at this pressure, to allow for Xenon feed system venting

SEPS-344//T

Intermediate pressures within the SEPS (e.g. between each FCU and SEPT) shall be defined by the contractor. All elements within the SEPS exposed to these pressures shall be demonstrated to be compatible with them, including the proof and burst margins as specified in SEPS-17.

3.2.2 Leakage

SEPS-18//T

Each FCU shall have an internal leak rate of less than 1.4 x 10-5 scc/s GHe at any pressure up to MEP. This requirement shall also apply to each FCU valve independently

SEPS-19//T

Each FCU shall also have an internal leak rate of less than 1.4 x 10-5 scc/s GHe when subjected to internal evacuation on its inlet and under ambient external conditions (i.e. a reverse pressure condition of up to 1 bar at the outlet and vacuum conditions on the inlet)

SEPS-20/MPB-4588/T

Each thruster plus FCU shall have a global external leak rate (excluding the effects of FCU internal leakage identified above) of less than 1 x 10-6 scc/s GHe

SEPS-21//T

The above leak rates are applicable at any point within the pressure and temperature ranges specified within this document. The only exception is that the leak rate corresponding to internal evacuation under ambient external conditions is required at ambient clean room temperatures only

SEPS-866//T

Each FCU shall remain leak tight, with an overall leak rate leak less than that specified in SEPS-19, during exposure to the launch environment specified in Section 4.2.2.

3.2.3 Propellant Specification

SEPS-24/MPB-4578/T

The SEPS shall be compatible with Xenon grade 4.8 ( 99.998% )as detailed below (TBC). For any contaminant not specifically detailed in this table, the SEPS shall be compatible with this at any level up to 0.002%


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The worst case Xenon quality which can be provided to the SEPS shall be identified by the contractor. The maximum allowable level of all contaminants of concern shall be individually specified.

Grade Impurities

(gas Phase)

99.998% (N4.8)

(vol. PPM)

Carbon Tetrafluoride <0.1

Hydrogen <1

Nitrogen <10

Oxygen <2

Hydrocarbons <0.1

Moisture <2

Carbon Dioxide and Carbon Monoxide

<2

3.2.4 FCU Configuration

SEPS-22//T

All valves within the SEPS shall automatically close in case of any failure.

SEPS-23//T

Each FCU shall provide at least 2 independent serial inhibits between their inlet and the ambient external environment.

SEPS xenon inlet (FCU inlet ) shall be protected from particulate contamination by apropriate inlet filters.

3.2.5 Redundancy

SEPS-26/MPB-4537,MPB-4600/

The SEPS shall provide 4 thrusters (including 1 neutraliser per thruster) + FCUs, of which one is for redundancy.

SEPS-27//A,R

Each thruster shall be connected to its own dedicated FCU.

SEPS-28/MPB-4600/A,R

The PPUs (number and configuration), including any electronics included in separate units as identified in SEPS-33 below, shall provide sufficient redundancy such that operation of 3 thrusters is still achievable in any of the combinations identified in this document, in the event of any single failure within any part of the SEPS. Internal redundancy within the PPUs may be used to achieve this requirement.

SEPS-29//A,R

No internal redundancy is required (by the Customer) within each thruster + FCU combination or within the PPUs, with the following exceptions:

• PPU internal redundancy is permitted as defined in SEPS-28 above

• Redundant MIL-STD-1553B bus

However, this requirement does not preclude the SEPS Contractor proposing schemes which utilise internal redundancy in order to meet the overall SEPS redundancy requirements.


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SEPS-30//A,R

Operation of any of the available thruster combinations shall exhibit the same operational characteristics.

SEPS-31/MPB-4483/T,A

It shall be possible to operate the thrusters singly (up to 145 mN) or in any pair combination compatible with the available power level.

SEPS-32//A,R

There shall be no single possible failure mode within the SEPS which can result in hazardous failure propagation to the remainder of the spacecraft.

SEPS-33/MPB-3654/A,R

Failure of one element or part shall not prevent any other redundant element or part from performing its intended function, nor the SEPS from meeting its operation and performance requirements.

3.2.6 Thruster Neutralisers

SEPS-35//I

Each thruster shall be equipped with a neutraliser device to prevent charging of the spacecraft.

SEPS-36/MPB-4541,MPB-4485/T,A

Each neutraliser shall be able to deliver independently the necessary neutralisation current corresponding to two thrusters simultaneously operating at their maximum thrust level (as defined below).


The SEPS shall allow the operation of any thruster, or pair of thrusters, in conjunction with the neutraliser from any other thruster (i.e. any neutraliser may be selected to be active and operational, independent of the operational thruster selection).


Neutraliser end-of-life shall be observable / predictable from housekeeping data / SEPS telemetry

3.2.7 SEPS Operations and Modes

3.2.7.1 Introduction

The SEPS Operations and Modes are seperate from the MEPS / MCU modes. These modes are controlled by the PPUs. Mode transition commands are recieved from the MCU. All operations within the modes are controlled by the PPUs.

3.2.7.2 SEPS Modes

SEPS Mode Diagram.


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OFF Stand-by

Discharge only

Remote

Thrust

Venting

Configuration Outgassing

OFF Stand-by

Discharge only

Remote

Thrust

Venting

Configuration Outgassing

SEPS-868//T,A,R

The SEPS shall provide as a minimum the functional modes identified below for each thruster and the corresponding FCU, power supplies and control unit (see SEPS-40 below) (additional modes may be proposed by the Contractor if required to meet specific needs with respect to their SEPS design).

Note: the Contractor may propose alternative actual modes for the SEPS, provided that these provide the equivalent level of functionality compared with that defined below.

SEPS-869//T

OFF: All parts of the SEPS are switched OFF. Note:- switch off will be a high power relay command.

SEPS-870//T

Stand-by: The SEPS control unit(s) are powered; all other supplies are disabled

SEPS-871//T

Configuration: Switching between selected thrusters and/or neutralisers is permitted, but all other supplies are OFF

SEPS-873//T

Venting: All valves for one or more FCU are opened simultaneously to allow venting of the feed system; all other supplies are disabled

SEPS-872//T

Discharge only: The main discharge is ON, but with no thrust produced

SEPS-874//T

Thrust: The thruster is operating, and generating thrust at the required level

SEPS-5333//T

Outgassing mode: The SEPS supplier shall provide any special needs for this mode including duration and power requirements.


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SEPS-875//T

Neutraliser ON: The selected neutraliser is operating at the required neutralisation current

SEPS-876//T

Neutraliser OFF: The selected neutraliser is OFF

SEPS-878//T

Remote: All SEPS power supplies are directly available from the spacecraft, and their settings and status can be modified by commands from the spacecraft. Note, this is to cover manual and test operations.

SEPS-877//T

The neutraliser ON and neutraliser OFF modes shall be available for each neutraliser, independent of the mode status for the thruster, except as detailed below in SEPS-884

SEPS-884/MPB-4544/T

It shall not be possible to select neutraliser OFF on all neutralisers in the event that any thruster is in Thrust Mode; similarly, it shall not be possible to select Thrust mode unless at least one neutraliser is ON.

3.2.7.3 Nominal Operations

SEPS-39//T,A

Either one or two thrusters shall be operable simultaneously. There shall be no restrictions on these operations, over the full operating range identified in this document.

SEPS-988//T,A

All thruster firing operations shall be achievable with the thrusters separated by any distance between 0.5 m and 1 m, measured between the thruster centrelines (assuming the thrusters are parallel to one another). This shall include simultaneous operation of any 2 thrusters, and any thruster / neutraliser combination, as identified in this specification.


During simultaneous two thruster firing operations, the thrust vectors of the two operating thrusters shall be nominally parallel, with each thrust vector varying by up to +/-2.5 degrees around the nominal overall thrust vector centreline. Any interactions between the two operating thrusters shall not cause deviations from values identified in this specification. Ref SEPS-154 and SEPS-155.

SEPS-40//T

All the SEPS operations within the modes defined in Section 3.2.7.2 (including start-up, regulated thrust management, shutdown, and beam-out management) shall be controlled by the PPUs this shall include all actions required to establish these modes following receipt of the corresponding mode transition commands from the spacecraft.

SEPS-353//T

It shall be possible to alter the thrust level at any time, and all operating parameters shall be capable of modification from the spacecraft.

SEPS-354//T

It shall be possible to achieve different thrust levels and operating conditions on each of the operating thrusters, including during simultaneous thruster operation.

SEPS-848/MPB-4549/T

The SEPS shall provide closed loop control of the flow rate through each FCU. This may be either direct or indirect (e.g. using thermal or thruster operational data); however, whichever method is chosen, this shall still ensure compliance with all parts of this specification.


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SEPS-355//T

The PPUs shall comply with the redundancy requirements above (i.e. they shall continue to provide the necessary control functionality for all operating modes in the event of any single failure, including failures within the control unit(s)).

SEPS-43//T,A,R

All SEPS operations shall be capable of being performed completely autonomously under the overall control of the spacecraft, using only SEPS telemetry with no ground visibility or commands. The SEPS shall not require any ground intervention for a period of at least 14 days.

SEPS-46/MPB-4550/T

The PPU and FCU shall provide sufficient power and Xe flow control accuracy to ensure the requirements of this document are met, for all operating regimes identified in this document, over the lifetime of the SEPS.

SEPS-861//T

The PPU shall be switched ON and OFF using high level commands, and the corresponding status shall be provided by direct TM.


The xenon system shall permit purging flows through the cathode, neutraliser and main flow, as needed during LEOP and NECP with flow rates equivalent to the max thrust level.

3.2.7.4 Beam-Out Management

A beam-out event is defined as a temporary loss of thrust on any operating thruster (shut down of the beam current), with the main discharge still continuing to operate.

SEPS-41//T

The SEPS shall include unambiguous means for detection of and recovery from beam-out events; these events shall be reported to the spacecraft.

SEPS-356//T

Any resulting attempted restart of a thruster following a beam-out shall not contravene any of the other requirements within this specification.

SEPS-357//T,A,R

A beam-out counter shall be provided, and beam-out recovery shall be terminated in the event of the number of consecutive attempted restarts (after a beam-out) exceeding [configurable value] during [ configurable value] minutes after any beam-out, or some lower restart [configurable value] number (or higher frequency) if deemed necessary by the Contractor to ensure the SEPS integrity.

SEPS-5859//T

The beam-out counter shall be time referenced and re-setable.

The configurable parameters as defined in SEPS-357shall be fully programable (in flight).

SEPS-5861//T

The beam-out counter only needs to store the count value for a predetermined period TBD and not between off modes.

3.2.7.5 Failure Management

SEPS-44//T

The SEPS shall automatically shut down in the event of any failure which could jeopardise the spacecraft (e.g. neutraliser failure, PPU input overcurrent, etc.).


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The SEPS shall include unambiguous means for detection of and the resulting actions for all abnormal events; this shall include all events which would result in the need for autonomous shutdown of either a thruster functional chain or the complete SEPS, either by the SEPS itself or by command from the spacecraft. All such events shall be reported to the MCU. It shall be possible to reconstruct events leading to any abnormal event from the TM available from the SEPS.

SEPS-883//T

The SEPS internal failure detection shall include all limit checking of the operating parameters. In the event of these limits being violated, the SEPS shall automatically shut down, and report back to the spacecraft which limits were violated.

SEPS-5245//T

The SEPS internal failure detection shall report back to the spacecraft a warning when the measured values are within 10% TBC of a fault condition (corrisponding to linits defined in SEPS-883 ).

SEPS-885/MPB-5056,MPB-5055/T

When in Thrust mode, the SEPS control units (PPUs) shall transition to Discharge Only mode if the communication link between the MCU and the SEPS is broken in either direction. This communication link shall be monitored by a suitable watchdog / FDIR type function (TBD) .

SEPS-881//T

In the event of a neutraliser failure during any operations where only 1 neutraliser is operating, which results in loss of neutralisation of the thruster plume(s), all operating thrusters shall be transitioned to Stand-by mode immediately. The SEPS shall provide hardwired links between the relevant controllers and PPUs to achieve this, without requiring any activity from the remainder of the spacecraft.

3.2.7.6 Additional Operational Requirements

SEPS-48/MPB-4480,MPB-4479/T

It shall be possible to open any combination of FCU valves / flow controller simultaneously, from any single valve/ flow controller actuation up to and including all FCU valves / flow controllers on all thrusters, for test, venting and purging operations on ground or in orbit.


The SEPS shall include the ability to clear any shorts between the thruster grids, by the application of suitable voltage and current levels to the grids. This facility shall be available even in the event of any single failure within the SEPS. The grid clearing facility shall not dimension the PPUs.

SEPS-5246/MPB-4573/T

The use of the grid clearing facility shall not damage or degrade any functionality of the PPU.


The use of the grid clearing capability shall not result in any degradation in the SEPS availability or performance, which would violate any other requirements of this specification. This activity shall only be available using a dedicated additional mode or in Remote mode.

SEPS-859//T,A

The User Manual shall identify any operational constraints to be applied either before or during SEPS operations (e.g. outgassing activities before first operations in space), and any timing criticalities for these activities.


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SEPS-860//T

The total elapsed time to complete all SEPS initial conditioning activities from first application of power to first operation firing, should not exceed 2 weeks TBC

SEPS-5334/MPB-4490/T,A,R

The availability of the SEPS during powered flight shall be better than 98 % over a 24 hour period.

3.2.7.7 SEPS Software / Firmware

SEPS-4915/MPB-4565/R

The SEPS flight Software/ Firmware shall comply with the requirements of the following documents:

• AD 01 General Design and Interface Requirements (GDIR)

• AD 07 SW PA Requirements for Subcontractors

• AD 08 PA Requirements for Subcontractors

• AD 20 Onboard Software Definition Document (OBSDD)

• AD 16 Operational and Automony Requirement Specification

SEPS-6057//T

The SEPS Software / Firmware shall implement a 1553B communication bus to communicate with the MCU

SEPS-6058//T

The SEPS Software / Firmware shall Perform all control and monitoring functions required to enable the functionality described in Section 3.2.7.2, Section 3.2.7.3, Section 3.2.7.4, Section 3.2.7.5 and Section 3.2.7.6,

SEPS-6136//T

All the SEPS Software / Firmware parameters shall be modifiable in flight .

3.3 Performance Requirements

SEPS-362//T,A,R

The SEPS shall comply with all of the performance requirements below, taking into account the following:

• Errors associated with equipment tolerances (including the PPU electronics), command accuracy, telemetry accuracy, and any other aspect of the SEPS which may introduce performance variability

• Unit to unit variability and worst case performance

• Measurement errors (including at least thrust, flow rate, and power where appropriate)

• Degradation over life

SEPS-4916//T,A

The SEPS shall comply with the following performance requirements over all the environmental requirements as defined in this specification

SEPS-363//T,A

For EOL performances specified below, EOL shall correspond to the performance after the number of hours of thruster operation (at an assumed average thrust of 137 mN) defined in SEPS-67. The


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specified performance at any intermediate point of the thruster life shall be taken from a linear interpolation of the requirements defined below at BOL and EOL.

3.3.1 Thrust

SEPS-55/MPB-4466/T

The thrust (for each thruster) shall be throttleable to any level between 75 and 145 mN, at any point in the mission life.

SEPS-56/MPB-4467/T

The stabilised thrust accuracy for each thruster (absolute difference between commanded and achieved stabilised thrust levels, as defined below) shall not exceed 3 mN

SEPS-57/MPB-4473/T

The commanded thrust quantization (size of commanded discrete thrust steps) shall not exceed 0.3 mN

3.3.2 Specific Impulse


The specific impulse for each thruster + FCU shall be greater than the following:

• Isp ≥ 4522 s at 75 mN, ≥ 4630 s at 145 mN at BOL

• Isp ≥ 4500 s at 75 mN, ≥ 4608 s at 145 mN at EOL

The minimum allowable specific impulse at intermediate thrust levels is shown in Figure 3.3-1 below.

SEPS-368//T

The above requirements shall include all flows (including all cathode, neutraliser and main flows).

y = -1.1256E-02x2 + 4.0214E+00x + 4.2837E+03

y = -1.1200E-02x2 + 4.0014E+00x + 4.2624E+03

4400.00

4450.00

4500.00

4550.00

4600.00

4650.00

4700.00

75 80 85 90 95 100 105 110 115 120 125 130 135 140 145

Thrust (mN)

Spec

ific

impu

lse

(s)

BOL EOL Figure 3.3-1: SEPS Specific Impulse Requirements


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3.3.3 Power Consumption

SEPS-62/MPB-4468/T

The power required by each thruster + FCU, in conjunction with its power supplies, shall be less the following at the PPU input:

• 2723 W at 75 mN, 5004 W at 145 mN at BOL

• 2742 W at 75 mN, 5041 W at 145 mN at EOL.

For intermediate thrust levels, the power required at the PPU input shall be lower than that shown in Figure 3.3-2 below.

y = 33.357x + 163.21

y = 32.843x + 278.79

2000

2500

3000

3500

4000

4500

5000

5500

75 80 85 90 95 100 105 110 115 120 125 130 135 140 145

Th rust (m N )

Pow

er (W

)

BO L EO L Figure 3.3-2: SEPS Power Requirements

3.3.4 Power Dissipation

SEPS-63//T

Each PPU shall not dissipate more than 338W for any of the operating regimes identified in this specification

SEPS-890//T,A

The Contractor shall quantify and provide, in tabular or graphic form, the relationship between PPU efficiency and PPU temperature, as measured at its reference point, over the operational range of the SEPS thrusters.

SEPS-367//T,A

The above power dissipation and efficiency figures shall include all power electronics, including items housed outside of the main PPU (see SEPS-332 and SEPS-333 above). The proportion of the power dissipated by any electronics housed outside the main PPU, and the corresponding efficiency figures as a function of the corresponding unit temperature, shall be declared by the contractor.


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SEPS-369//T

The power dissipated by each FCU and each thruster shall be declared by the Contractor for each operating mode.

SEPS-370//T

The above power dissipation figures shall be declared as a function of thrust, over the SEPS operating regime identified in this document.

3.3.5 Performance Models

SEPS-64//T,A

The performance mathematical models (as defined in the SOW) shall include the following:

• Specific impulse as a function of thrust (including all Xe flows) & life

• PPU input power as a function of thrust & life

• PPU dissipation as a function of thrust & life

Confidence levels in these models, based on test data where available, shall be declared. Systematic and random errors shall be separately identified.

SEPS-65//T,A

The Contractor shall identify within these performance models the proportion of the total flow which is consumed by the neutraliser.

SEPS-5862//T,A

The Contractor shall indicate within these performance models Neutraliser flow when using 1 or 2 netralisers for twin thruster operation.

3.3.6 Response Time

SEPS-58/MPB-4474/T

The thrust stabilisation time (time from thruster beam being enabled to commanded thrust being reached, within the accuracy defined above) shall be less than 1 minutes (TBC)

SEPS-59//T

The total thruster initialisation time (time from SEPS being off to thruster achieving the commanded thrust level) shall be less than 30 (TBC) minutes

SEPS-60/MPB-4475/T

Any change in commanded thrust levels shall be realised within 1 minute of the command being received by the SEPS

3.3.7 Beam-Out Limits

SEPS-888//T

Following any beam-out event, the thruster shall recover to the previously commanded full thrust level within 2 seconds (TBC) from the start of the beamout.


The accumulated down-time due to beam-out events, including recovery to full thrust as specified above, shall not exceed 0.05% of the total firing time.

3.3.8 Thrust Vector

3.3.8.1 Alignment Requirements

SEPS-154/MPB-5057/T

The thrust vector radial offset shall be less than 1 mm compared to the thruster centreline (defined on the thruster ICD)


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SEPS-155/MPB-5057/T

Thrust vector angular offset shall be less than 1º compared to the thruster centreline (defined on the thruster ICD). This shall include the thrust vector stability figures defined in Section 3.3.8.2

3.3.8.2 Stability Requirements

SEPS-78/MPB-4477,MPB-4476/T

Thrust vector stability shall be better than the following (the following figures are half cone, referenced relative to nominal thrust direction):

• <0.3º thrust vector deviation (maximum value including stabilisation period)

• <0.1º thrust vector deviation averaged over any period between 1 minute and 30 days of thruster operation, when operating at constant thrust


The stabilised thrust vector magnitude, averaged over a period of 10 sec, shall not change by more than 0.5 mN in any period up to 1 hour.

3.3.9 Thruster Plume

SEPS-66/MPB-4558/T

The thruster plume beam divergence (including 95% of the total ion beam current) shall be less than 25º half cone angle, at all stages of the thruster life, and for any of the operational conditions defined in this document

3.3.10 SEPS Life

3.3.10.1 Operational Life


Each individual thruster and FCU (and dedicated electronics where appropriate) shall be able to achieve the following life requirements (the following figures include qualification factor of 1.5).

• 10.21 MNs total impulse

• 20754 hours

The above figures are flight only, the total impulse and numberr of hours accumulated on each thruster during acceptance ground testing shall be added to the numbers above for life deterimation and verification purposes.

The graph below shows the worst case flight thruster firing profile TBC


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0

0.02

0.04

0.06

0.08

0.1

0.12

0.14

0.16

0 500 1000 1500 2000 2500

Time (days)

Thru

st (p

er th

rust

er, w

orst

cas

e) (N

)

Single thruster operation Two thruster operations

SEPS-929//T,A

Each neutraliser shall be able to achieve the above life requirements with respect to operating hours, when supplying sufficient current to neutralise 2 thrusters operating simultaneously at any point in the thrust range defined in Section 3.3.

SEPS-928//T,A

The above life requirements are strictly dependent on the SEPS design imposing no constraints on the thruster or neutraliser availability, either nominally and in case of any single SEPS failure, as identified in Section 1.3, Section 3.2.5, Section 1.1 and SEPS-37. In the event that any operating constraints are imposed, the Customer reserves the right to re-evaluate the life requirements accordingly.

SEPS-68//T

Each thruster, FCU and its PPU supplies shall be capable of at least 500 operational cycles post launch (including qualification margin)

SEPS-69//R

The above cycling requirements do not include restarts due to beam out events; the Contractor shall assess the number of beam outs to be expected, and the corresponding equivalent additional restart requirements

SEPS-376//T

The PPUs shall be compatible with the above life requirements


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SEPS-385//T

The SEPS shall be compatible with 1,000,000 pressure cycles applied at the FCU inlet (including qualification factor of 2). The magnitude and pressure rate change for these cycles is defined in Section 4.3.4.1.

SEPS-386//R

Any element of the SEPS shall be considered to have reached the end of its life if it results in any of the requirements within this specification being violated, or if it results in failure of any SEPS equipment. This definition of end of life shall include (but not be restricted to) the impacts of electron back-streaming into thruster which may result in thrust, specific impulse, input power, thermal, mechanical or any other performance degradation beyond the limits set within this specification.

SEPS-73//A,R,S

The Contractor shall supply their estimate of the life capability of the SEPS in terms of both total impulse and firing time; this shall be substantiated by test data as far as is possible, and shall consider all items of the SEPS which are subject to life limitations.

3.3.10.2 Design Life

SEPS-100/GDI-53/T,A

The SEPS shall perform within the requirements of this specification without degradation,

• On ground = 5 years

• During orbital transfer = 6.6years

SEPS-101//R

Maintenance during storage and long periods of non operationl periods during flight shall be as limited as possible and, if required, shall be identified by the Contractor for approval by the Customer.

3.3.10.3 Harness and Pipework Accommodation

SEPS-51//T

The harness and pipework set associated with each thruster shall present less than 4 Nm (TBC) torque resistance, when subjected to rotation of the thruster (on suitable gimbals) over a range of up to ±17º (TBC) in 2 axes, with the FCU and PPU hard mounted to the spacecraft structure

SEPS-52/MPB-4555/T

The harness and pipework set associated with each thruster shall be compatible with the following mechanism in flight operations (TBC):

• number of large slews ≥ +/- 17°: 3000 (including on ground cycles)

• number of slews ≥ +/- 5°: 3000 (including on ground cycles)

• small increments of +/- 0.1°: 170000 evenly distributed over a pointing range of 2.2° (TBC) from a start position of (TBD)

• number of slews to reference / end stops: TBD

The rotations may be around any point, but shall be within the overall angular range specified above.

A qualification factor of 2 (TBC) shall be applied to these figures.

SEPS-4829//T

The harness and pipework set associated with each thruster shall be capable to cope with angular movements up to TBD degrees in all directions greater than the operational requirements defined in SEPS-52. These movements are required to enable arming access to the TPA hold down


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mechanism and are not part of the normal operational requirements described in SEPS-51 and SEPS-52. To accommodate these additional movements it may be necessary to remove harness and / or pipework fixings.


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4 SUBSYSTEM AND UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS

This section defines general, mechanical, thermal and electrical design and interface requirements applicable to the equipment. The general requirements are contained in AD01; This section then details additional specific requirements for the SEPS.

4.1 Design Criteria

4.1.1 Proof and Burst Pressures

4.1.1.1 Proof Pressure

Refer to AD 01 GDI 129 to 133.

4.1.1.2 Burst Pressure

SEPS-390//T

All pressurised items shall have demonstrated burst factor of 2.5; for all pipework and fittings, a burst margin of 4 shall be demonstrated. The SEPS equipments shall withstand, without rupture, a pressure of 2.5 × MEP (Maximum Expected Pressure), or 4 x MEP (Maximum Expected Pressure) for pipework and fittings (throughout the qualification temperature range).

4.1.1.3 FCU MEP (Maximum Expected Pressure) Definition

SEPS-392//R

For the FCU inlet, the above requirements shall be referenced to the 10bar MEP (Maximum Expected Pressure) identified in SEPS-16 above.

4.1.2 Mechanical Design and Interface Requirements

4.1.2.1 Design Requirements

4.1.2.1.1 SEPT (thruster) Mechanical Characteristics

SEPS-6142//T,A,I,R

The SEPT shall be attached to the TPM mounting face, at the base of the thruster using suitable fixings (TBD).

SEPS-6143//R

The max allowable envelope volume for each SEPT is 378mm dia (centred on the thruster centreline ) with maximum height from mounting face of 314mm.

4.1.2.1.2 Attachment Requirements

SEPS-149//T,A

The attachment points shall provide a controlled surface contact between the units and the structure to allow control of thermal conditions on the units as well as electrical bonding. This contact shall be maintained under all operating conditions, taking into account loading resulting from the different thermal coefficient of expansion between dissimilar materials.

SEPS-150//T

The mechanical mounting interface shall be consistent with the thermal and EMC/ESD Design and Test Requirements Specification ref. AD 03. In particular, the contact area shall be free of paint.

SEPS-151//R

Thermally dissipative units shall have proper provisions to allow implementation of interface filler between their base-plate and the supporting structure.


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4.1.3 Thermal Design and Interface Requirements

4.1.3.1 Thermal Interface Requirements

SEPS-5952//R

The Contractor is resposible for the thermal design of the SEPS which includes the SEPT, FCU and PPU's

SEPS-175//A,R

Internal units shall be designed with an emissivity > 0.8 (black) (as specified in AD01). For units for which this is not possible (e.g. thruster), all thermo-optical properties are to be provided

SEPS-891//A

Where a specific finish is selected (e.g. a paint), it shall be demonstrated that this is compatible with the range of conditions experienced over the complete BepiColombo mission.

SEPS-177//T

Any thermal control internal to the SEPS (thruster, FCU, etc.) has to be managed by the SEPS itself, and shall not rely on outside monitoring or control

SEPS-178//I,R

The SEPS shall allow for the attachment of thermal monitoring devices on at least the thruster mounting interface, FCU interface and PPU base plate.

SEPS-6744//T,A

The SEPS unit's interface temperatures (operational) are as follows (TBC):

FCU -30 to + 65°C

Thruster -50 to + 190°C

SEPS-6745//T,A

The SEPS unit's interface temperatures (non-operational) are as follows (TBC):

FCU -40 to + 75°C

Thruster -60 to + 200°C

4.1.3.1.1 Thruster Conductive Thermal Interface

SEPS-179//T,A

The thruster shall be capable of operation when mounted thermally isolated from its support; it shall be capable of operation over the operating range identified in this document, with no reliance on thermal conduction back through its mounting for thermal control. The temperature of this support shall not exceed that defined in SEPS-6744 when two SEPTs are operating simultaneously and the worst case solar load is included.

SEPS-5951//T,A

The SEPT harness shall not conduct or dissipate more than 5W TBD back into the MTM.

4.1.3.1.2 Thruster Radiative Thermal Interface

SEPS-5946//A,R

The SEPTs are arranged symmetrically about the main engine on the +Z side of the MTM. When performing his thermal analysis, the Contractor shall take into account the radiative environment defined in SEPS-5947, SEPS-5948 & SEPS-5949 below.

SEPS-5947//A,R

• The SEPTs have a view to the external MLI on the underside of the MTM. It has the following thermo-optical properties (all values are TBC):


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Emissivity = 0.87

Diffuse reflectivity (infra-red) = 0.13

Absorptivity = 0.5

Diffuse reflectivity (solar) = 0.5

SEPS-5948//A,R

• The SEPTs have a view to the main engine nozzle on the underside of the MTM. It has the following thermo-optical properties (all values are TBC):

Emissivity = 0.73

Diffuse reflectivity (infra-red) = 0.27

Absorptivity = 0.91

Diffuse reflectivity (solar) = 0.09

SEPS-5949//A,R

• The following radaitive environment temperatures apply:

MLI: -175 / +380°C (TBC)

Main Engine Nozzle: -150 / 450°C TBC

The customer shall provide the geometry of this area

4.1.3.1.3 Thruster Thermal Mathamatical Model

SEPS-5955//A,R

The Contractor shall substantiate the thermo-optical properties and the conductive couplings used in his model.

• The Contractor shall define his thermal model using the MTM co-ordinate system defined in AD01 GDIR section GIR-3977.

• The Contractor shall use node numbers in the range 41500 - 41600, and for the electrons units (eg PPUs or other) 42500-42520

.

A reduced thermal model in ESARAD/ESATAN format as input to the MTM thermal model

The detailed thermal model of a unit shall be verified and correlated with a thermal test in accordance with the AD01 GDIR GDI-335, GDI-338 and GDI-340.

SEPS-180//T,A

The PPU shall dissipate all heat through the baseplate interface to a total of 3 kW/m2 (TBC)


The SEPS shall be capable of all operations identified in this specification in the presence of the following solar flux conditions onto the thrusters. The solar illumination angles specified below are relative to an axis normal to the thrust vector direction for each thruster (i.e. 0 degrees corresponds to side illumination of the thruster normal to the thrust axis, and 90 degrees corresponding to illumination along the thrust axis, on the exposed thruster surface (grid face)).

• >0.7 AU - illumination from any angle


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• 0.47 to 0.7 AU - illumination at any angle from 0 up to 46 degrees (TBC)

• 0.3 to 0.47 AU - illumination at any angle from 0 up to 28 degrees (TBC)

SEPS-182//T,A

The SEPS shall survive illumination of the thrusters from any angle, at any distance from 0.3 AU upwards, for non-operational cases for a maximum period of 3 minutes.


Solar irradiation shall not give rise to ion thruster outages, such as arcing in the grid system.

4.1.3.2 Thermal Design Requirements

SEPS-185//T

The units shall not exhibit any high temperature failure modes that can cause hot spots that will propagate inside or outside the units to any other assembly or impact on the performance of any internal protection circuits intended to limit such propagation or limit consumption.

SEPS-187//T,A

Hot spots on the external surface of the units shall be taken into account at the unit level. In designing the unit and ascertaining the optimum flow paths, the unit design shall take due account of the method of mounting and the relative exchanges with the environment by both conduction and radiation.

The objective of the unit thermal analysis is to demonstrate that internal components have acceptable temperatures when the unit itself (i.e. case or base plate) is at its operating temperature limits, with a reasonably representative distribution of the heat flow to the external environment.

SEPS-5977//A

The SEPS internal units including the Pipework & Harnesses (i.e. from the PPU-TPM): shall be compatible with the thermal environment of the MTM.

The SEPS Pipwork & Harnesses between the PPU and the TPM are fully enclosed when within the MTM engine bay, an MLI blanket located at the level of the TPM to SEPT interface ensures that there is no direct view between the TPMs and the SEPTs and the MTM main engine. In addition, this means that the Pipwork & Harnesses do not have a direct view to space. However, they never see any solar flux, either. Within the engine bay, a dedicated heat shield covers the hot parts of the main engine.

The MTM structure within the engine bay is also covered with MLI.

The Customer will provide the engine bay geometry.

SEPS-5981//R

This MLI shall be supplied by the Customer. Mass and configuration to be shown in the relevant ICD.

SEPS-5980//T,A

The SEPS thermal design, undertaken by the Contractor, shall take into account the following radiative environment parameters shown below in SEPS-5983 and SEPS-5984.

Engine Bay, the following proerties relate to the internal surfaces underneath the external MLI (this is where the TPM's are housed):

Emissivity: 0.05

Main Engine Heat Shield:

Emissivity: 0.25


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The radiative environment temperature range that shall be considered for the MTM engine bay is -100 to +100°C (TBC).

SEPS-5978//T,A

The SEPS external harness (i.e. along the side of the thruster): shall be compatible with thruster firing and worst case solar illumination, as well as main engine firing ( SEPT off) thermal enviroment. TBC

SEPS-6138//T

The SEPS harness dissipation per unit length shall not exceed 2W/m (TBC)

4.1.4 Electrical Requirements

The following section defines the general electrical interface requirements

4.1.4.1 General Requirements

SEPS-198//T,R

All electrical power interfaces to the SEPS, shall be managed via the PPU.

SEPS-200//I,R

All high voltage (>200 V) harnesses shall be double insulated.

SEPS-201//T,R

A suitable qualification process shall be established for high-voltage components and harness

SEPS-203//T,I

After final electrical connection of the SEPS on the spacecraft, it shall be possible to verify continuity of all electrical lines within the SEPS under ambient cleanroom conditions

4.1.4.2 Power Consumption / Dissipation

SEPS-205//R

The power allocation for each unit shall be defined in the unit specifications. It shall cover all the operating modes and the mean and peak (long and short) figures. Note that:

o Mean represents the average consumption over 5 minutes (inclusive of heater power)

o Short peak represents the power demand not exceeding 1 msec

o Long peak represents the power demand not exceeding 100 msec

SEPS-5317//T,A

The SEPS maximum power requirements shall be:

• 10.082kW on the 100V bus

4.1.4.3 Power Interfaces

Refer to AD01 Section 3.6.2.4.2.1

SEPS-215//I,R

No fuse protection shall be implemented

SEPS-217//T

The SEPS shall assume an OFF configuration upon application of power in nominal conditions.

SEPS-219//T

When a unit is internally redundant, and the supply to one of the internal redundant modules fails, the unit shall be able to fulfill all its performances and functionality when switched to the redundant part with no degradation of performance.


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4.1.4.3.1 100 Volt Bus Definition

The SEPS shall be compatible with the following characteristics from the 100V regulated bus.

SEPS-211//T

The SEPS shall be fully compliant with the requirements of this specification for input voltages in the range 98 to 102V (i.e. +/-2% regulation on the nominal 100V)

SEPS-4836//T

The SEPS shall continue to operate at any voltage in the range 95.1V to 110V (TBC) (extended voltage operating range). During any operations over this extended voltage operating range, the SEPS performance may be out of specification

SEPS-4837//T

No undervoltage protections within the SEPS shall be triggered within the extended voltage operating range

SEPS-4838//T

The SEPS shall provide internal overvoltage protection, such that it shall automatically disconnect from the 100V bus in the event that the bus voltage exceeds the above extended voltage operating range for more than 100 microseconds.

SEPS-4839//T

The bus voltage protections shall be in the form of latch current limiters (LCL), or equivalent.

SEPS-6064//T

The total inrush current on the 100V bus to the SEPS shall be <30A peak, with a current rise rise time of di/dt<10A/usec. (TBC)

SEPS-4840//T

The SEPS shall not be irreversibly degraded for any standing or fluctuating voltage in the full range from 0 V to 110 V (TBC).

SEPS-4841//T

During SEPS start-up and SEPS operations, the SEPS shall not require any step load change of more than 3kW.

SEPS-4842//T

During SEPS start-up and SEPS operations, the SEPS shall not require any rate of increase of power by more than 10 kW/s

SEPS-4843//T

The MEPS shall not require more than 10.25kW from the 100V bus for operations at up to 290mN total thrust at any point in the mission.

SEPS-213//T

The PPU input of the UNPROTECTED UNSWITCHED 100 V ± 2 V HP Bus shall be single failure tolerant against overcurrent and short circuit.

4.1.4.4 Bonding, Grounding and Isolation

4.1.4.4.1 Bonding

SEPS-5851//T

Electrical bonding requirements are applicable and defined in AD03 EMC/ESD Design and Test Requirements Specification.


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4.1.4.4.2 Grounding

SEPS-5852//T

Electrical grounding requirements are applicable and defined in AD03 EMC/ESD Design and Test Requirements Specification.

4.1.4.4.3 Isolation

SEPS-5976//T,I

Electrical Isolation requirements are defined in AD03 EMC/ESD Design and Test Requirements Specification.

SEPS-4828//T,I

A DC isolation resistance of at least 10 Mohms at least 2 times the operating voltage for a duration of at least 1 minute between the non high voltage circuits and ground shall be maintained.

SEPS-260//T,I

A DC isolation of at least 1 Mohms at 100V between the primary and secondary grounds shall be maintained this shall be tested for a duration of 1 minute TBD.

SEPS-4826//T,I

A DC isolation resistance of at least 10 Mohms at 2 times the maximum operating voltage for a duration of at least 1 minute between the high voltage circuits and ground shall be maintained.

4.1.4.5 EMC

SEPS-5997//T,A,I,R

EMC requirements requirements are applicable and defined in AD03 EMC/ESD Design and Test Requirements Specification.

4.1.5 Design and Construction

4.1.5.1 Materials, Parts and Processing

4.1.5.1.1 Moisture and Fungus Resistance

SEPS-937//R

Materials that are nutrients to fungi shall be avoided. Where used, and not hermetically sealed, they shall be treated with a suitable fungicidal agent.

4.1.5.1.2 Magnetic Materials

SEPS-942//I,R

Magnetic materials shall not be used, unless approved by the Customer.

4.1.5.1.3 Ceramic Materials

SEPS-944//R

Ceramic materials or coatings that may crack or break under any combination of operating conditions or environments specified herein shall not be used.

4.1.5.1.4 Seals

SEPS-946//R

Elastomeric seals shall be used only as approved by the Customer.


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4.1.5.1.5 Standard and Commercial Parts

SEPS-950//I

Standard and commercial parts may be used if they do not degrade the reliability of the equipment and are in accordance with the requirements for approved materials and parts.

4.1.5.1.6 Finish

SEPS-952//R

The surface of the equipment shall be adequately finished to prevent deterioration from exposure to the specified environments that might jeopardise fulfilment of the specified performance.

SEPS-953//R

No cadmium, tin or zinc plating shall be used on any components.

4.1.5.1.7 Contamination and Cleanliness

• Contamination

SEPS-956//T,I

Operation of the equipment shall not result in the release or generation of particles entering the fluid passage or being exhausted externally to the equipment.

SEPS-957//I,R

The interior of the equipment shall be designed and fabricated to facilitate cleaning and prevent the entrapment of contaminants.

SEPS-958//I,R

Equipment shall contain no chips, slag, particulate matter, oil, grease, liquid or other foreign material.

• Equipment Cleanliness

SEPS-960//I

The equipment shall be assembled under cleanroom conditions, Class 100,000 or better.

SEPS-961//T,I

All equipments shall be measurably clean to equal or better than the levels shown below. For units exposed to the flight propellant, a sample (as described below) taken after passage through the equipment shall not exceed the listed particle count or distribution. The flushing media shall be Isopropyl Alcohol per AD14

SEPS-962//I Particle Size Maximum Allowable Count per first 100 ml Over 100 microns None 51 - 100 microns 5 Max ( non metallic ) 25 - 50 microns 50 max Less than 25 microns No silting Non Volatile Residue (NVR) Less than 1 mg/100ml

SEPS-963//I

The equivalent particle size of any particle is its maximum dimension (i.e. fibre length for fibres).

SEPS-964//I,R

Flight equipment shall not be subject to exposure to any liquids other than Isopropyl Alcohol per AD14, except as explicitly approved by the Customer.


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SEPS-965//T

All liquids shall be removed by flushing with Isopropyl Alcohol per AD14, and then purged with a dry inert gas, which has been demonstrated to be compatible with the SEPS. The water dew point shall be less than -55°C.

SEPS-966//T,I

After all cleaning procedures have been completed, the level of chemical contaminants retained in the equipment shall be such that correct functioning shall not be impaired or compromised throughout the operational lifetime.

SEPS-967//T

Cleanliness Verification Fluid Sample

100 ml of IPA to AD14, or 100 ml per 929 cm2 of internal surface area, whichever is the greater.

4.1.5.1.8 Fluid Compatibility

SEPS-969//A,R

The SEPS shall be compatible with the Xenon as specified in Section 3.2.3, cleanroom air, gaseous Helium and Argon, and any test fluids proposed to be used by the contractor.

SEPS-970//T,R

The Contractor shall ensure that all test media can be removed from wetted elements of the SEPS after delivery.

SEPS-971//R

All fluids used shall be agreed by the Customer.

SEPS-972//R

The use of halogenated solvents in contact with titanium alloys is prohibited.

4.1.5.1.9 Interchangeability

SEPS-976//I

All like parts shall have the same part number.

SEPS-977//I,R

Each equipment item shall be directly interchangeable in form, fit and function with other equipment of the same part number.

SEPS-978//I,R

The performance characteristics shall permit interchange with a minimum of adjustments and recalibrations.

SEPS-979//R

The equipment shall be of the same qualification status and reliability to meet interchangeability requirements.

4.1.5.1.10 Workmanship

SEPS-981//I

Workmanship shall be executed such that the design standard is not degraded or changed. At all points in the manufacture, production, integration, test, handling, storage and transportation, special steps shall be taken to maintain the design standard. The skill level of personnel is to be such that all aspects of workmanship shall ensure retention of the high reliability standards, with particular attention to the following:

• Free from blemishes, burrs, and sharp edges.


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• Required tolerances on dimensions.

• Compliance with designed radii of fillets.

• Adequate and correct marking of parts and assemblies.

• Thoroughness of cleaning, soldering, welding, brazing and finishing.

• Free from oxidation, cracks, undercuts, lack of fusion, incomplete penetration and sharp edges.

• Free from grease.

• Alignment of parts and assemblies, in accordance with specified requirements.

• Condition of surfaces, paying particular attention to impact and other damage.

4.1.5.1.11 Dissimilar Metals

SEPS-986//R

Contact of dissimilar metals with each other as defined in AD08 shall be avoided wherever possible. Protection against electrolytic corrosion which can result from such contact shall be provided by surface treatment of the metals. Dissimilar metal contact shall be approved by the Customer.

4.2 Environmental Design Requirements

Enviromental requirements are applicable and defined in AD02 Environment Requirements and Test Specification

SEPS-402//I,R

The equipment shall be designed with the required margins of safety to meet the design and performance requirements of this specification prior to exposure, during exposure and after exposure to the environments specified herein, as applicable. Environments experienced during fabrication, transportation and storage shall be controlled so as to be significantly less severe than the environments specified herein.

4.2.1 Pre-Launch (Including Spacecraft Level Tests, Storage and Transportation)

SEPS-405//T,I

The equipment shall meet the requirements of this specification after being exposed to the following pre-launch environmental conditions:

SEPS-407//I

Relative humidity up to 100% with conditions such that condensation takes place in the form of water and frost. There shall be zero internal humidity.

SEPS-408//I,R

Ambient pressure between sea-level (0.97 to 1.05 bar) and 1 × 10-5 torr. It is not expected to be able to fully operate the thruster in this pressure range; however, all allowable thruster operations, and any restrictions on operations of other SEPS units within this pressure range, are to be clearly identified by the contractor

SEPS-409//I

Ambient temperature range from -40°C to 65°C.

SEPS-410//A,I,R

The SEPS shall be transportable by air, ship and road and shall be packaged by the Contractor to withstand the shipment.


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SEPS-412//R

The SEPS units shall be capable of being stored for 12 months on the ground with up to the MEP (Maximum Expected Pressure) at FCU inlet, as defined in SEPS-16. Under these conditions the nominal storage temperature shall be 35°C maximum.

SEPS-406//R

The surrounding medium shall be air, nitrogen or helium.

SEPS-411//R

The SEPS units shall be subjected to the following environmental conditions due to spacecraft level ground tests:

SEPS-403//I

• Mechanical tests (1 set); the levels shall not exceed those identified in Section 4.2.2 _

SEPS-415//I

During spacecraft mechanical tests, all SEPS units shall be OFF.

SEPS-414//I

• Thermal vacuum test; this shall consist of 1 hot and one cold cycle, during which the levels shall not exceed those identified in Section 4.2.2.1.2.

SEPS-416//I

During spacecraft thermal vacuum testing, the PPUs shall be switched on and may be operated up to full power; however, the thrusters shall be OFF and disconnected, with the PPUs connected to suitable thruster simulators.

4.2.2 Launch

SEPS-418//T,I

The SEPS units shall meet the requirements of this specification during and after exposure to the following launch environmental conditions and with the FCU inlet pressurised at any pressure between ambient and MEOP, unless otherwise specified below.

4.2.2.1 All SEPS Units

4.2.2.1.1 Vibration Enviroment

SEPS-5990//T

Refer to AD02 Setion ET-15097 (Thruster)

4.2.2.1.2 Thermal Enviroments

SEPS-5991//T

Refer to AD02 Section ET-227

4.2.2.2 Thruster Specific

SEPS-281//T

Base Input Qualification Random Spectrum:


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Frequency (Hz) Level (g2/Hz) Slope (dB/Oct) 10 0.0236 -

10 to 70 - 6 70 to 200 1 - 200 to 215 - -29 215 to 455 0.5 - 455 to 2000 - -6

2000 0.026 -

SEPS-425//T

Base Input Acceptance Random Spectrum:

Note:

Acceptance level = Qualification factor - 4dB

Test durations shall be as follows:

- 180 seconds for Qualification

- 60 seconds for Proto-Flight

- 60 seconds for Acceptance

SEPS-4848//

Base Input Sine Qualification Vibration

SEPS-429//T

Frequency (Hz) Peak Level

5 - 100 38g

Sweep Rate 2 Octave / Minute

SEPS-434//T

Base Input Shock

The levels given in the table below apply in and out of plane for each unit

Frequency (Hz) SRS (Q=10) (g) Perpendicular SRS (Q=10) (g) Parallel 100 10 200 30 3000 2000 3000

10000 2000 3000

4.2.3 Cruise Phase Enviroment

4.2.3.1 Micro-Meteoroids

Refer to AD02 Setion ET-409


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SEPS-6114//T,A

The SEP thruster shall withstand the following acceleration grid damage scenarios, with TBD degradation in thrust, power and specific impulse:

• Removal of any 2 non-adjacent webs between grid holes

• Removal of 4 webs connecting 5 adjacent holes ("X" pattern)

• Removal of all webs connecting 7 holes in a hexagonal pattern

SEPS-6747//T,A

The SEP thruster Contractor shall determine the effect of the location (position on the grid) of the damage scenarios described in SEPS-6114.

SEPS-6115//T,A

The SEP thruster shall also operate with TBD degradation in thrust, power and specific impulse, in the event of the above damage also resulting in a consequential loss of screen grid material.

SEPS-6116//T,A

The ingestion of the resulting grid debris, with particles of up to 0.3 mm diameter (TBC) and TBD m/s velocities, shall not result in loss of the thruster, or TBD performance loss

4.3 Physical Characteristics

4.3.1 Configuration and Dimensions

SEPS-167//I,R

All relevant mechanical properties and interfaces shall be described within the specific unit interface control documents

4.3.2 Mass Properties

4.3.2.1 Mass

SEPS-160//T

The mass of the SEPS shall be less than 116.6 kg; this shall include all margins.

SEPS-161//T

The mass of each thruster shall be less than 7.5 kg without harnesses, and less than 8.1 kg including 1m of harness; these shall include all margins.

4.3.2.2 Centre of Gravity and MoI

SEPS-163//T

The unit centre of gravity shall be measured with an accuracy of ± 1mm (TBC).

SEPS-164//T

The unit moment of inertia shall be calculated with an accuracy of ± 5% (TBC).

4.3.3 Stiffness Requirements

SEPS-132//T

Each thruster shall have fundamental frequency of at least 130 Hz.

SEPS-133//T

All other items of the SEPS shall have a fundamental frequency of at least 100 Hz


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4.3.4 Interfaces

4.3.4.1 Xenon Feed System Interface Requirements

SEPS-80//

Each FCU shall be fed with gaseous Xe (at the FCU input) at a pressure of between 2.5 and 2.85 bar

SEPS-81//

The pressure at the FCU input may vary by up to 0.1 bar/s over the range specified above, during thruster firing and non-operating periods.

SEPS-82//

Each thruster shall achieve all the performance requirements, under the above inlet pressure conditions

4.3.4.2 Pipework and Harness Interfaces

SEPS-846//I

The SEPS pipework and harness shall only be attached to the thruster at its side.

SEPS-863//I,R

The SEPS harness between the PPU and thruster/FCU shall be split near the base of each TPM; connectors (or equivalent) shall be provided at this point to allow for disconnection of the thrusters, to enable connection to simulators for spacecraft level ground tests, followed by reconnection to the thrusters for flight.

SEPS-847//I,R

The Contractor shall identify the minimum necessary volume and accommodation requirements for the pipework and harness routed from the base of the TPM to the thruster, to ensure the requirements of Section 3.3.10.3 can be met.

SEPS-5330//I,R

The SEPT (Solar Electric Thruster ) shall be detachable from both the harness and the xenon feed pipework. to enable the thruster to be removed from the TPM with minimum disturbance of other hardware.

The estimated maximum total harness length from the PPU's to all thrusters and including cross strapping is 18 metres

4.3.4.3 Data Interface Requirements

Ref. SYS-3220 of the System Technical Specification shall be taken into account when designing the Data Interface due to the limitations of the data rate available

The data interface is between the PPU's and the MCU.

SEPS-84//T

The PPU shall provide HK TM of at least the following:

• All power supply actual voltages

• All power supply actual currents

• PPU input currents

• Status of all power supplies

• Status of all internal switches and relays

• Status of internal logics and modes

• Status of all internally redundant Items


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• Critical internal temperatures

• Thrust level

• SEPS Configurable Parameters

• SEPS Beamout Counter

• SEPS Mode

Sufficient TM shall be provided to enable autonomous on-board fault detection, diagnosis and recovery (including possible SEPS reconfiguration and restart)

SEPS-85/MPB-4486/T

Sufficient TM shall be provided to enable in orbit thrust determination, to within 1 mN of the actual delivered thrust for each thruster. The thrust shall be provided directly by the TM; the algorithm used to derive the thrust shall be provided by the contractor, and the parameters used for this determination shall also be provided in TM.

In the event of any autonomous switch over of any internally redundant items, sufficient telemetry shall be provided to allow analysis of the event.

SEPS-86//T

Sufficient TM shall be provided to enable in orbit flow rate determination, to within 7.5% of the actual flow rate.

SEPS-87//T

All TM shall be available at frequencies of up to 10Hz (TBC). All TM required for in-orbit performance determination shall be made available such that the above accuracies can be achieved at any time during SEPS operation.

SEPS-88//A,R

The Contractor shall identify the TM and TC quantity and timings required for successful operation of the SEPS.

SEPS-89//T

All SEPS TM and TC shall be managed by the PPU, via a redundant MIL-STD-1553B bus bus independently for each thruster functional chain, except any primary on/off relays which can be powered by relay telecommand.

4.4 Miscellaneous

4.4.1 Accessibility / Maintainability

SEPS-118//I,R

All electrical connections, including the final connection of the SEPTs to the power supplies at spacecraft level, shall be reversible in order to permit equipment repair / replacement where necessary

SEPS-864//

The PPUs shall not require physical access for any reason after integration (except in the event of a PPU failure necessitating removal of that unit).

SEPS-865//T,R

The SEPS shall provide for means of verifying correct final connection of the harnesses, without the need for any specialist test facilities or tools (other than those provided by the contractor). It shall not be necessary to initiate a plasma in any part of the thruster to achieve this final connection verification.


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4.4.2 Transportation, Handling and Storage

SEPS-124//I,R

Each item of the SEPS (thruster, PPU, FCU, pipework and harness) shall be transported separately, with sufficient documentation to allow final integration by the Customer.


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5 PRODUCT ASSURANCE

SEPS-325//A

The SEPS shall be designed, manufactured and tested in accordance with the PA requirements specified in AD-08. All products supplied against this specification shall be as safe as reasonably possible, and assessed in accordance with ECSS-Q-40B.

Documentation shall be supplied which addresses safety and EMC risks.

Safety warning labels are to be attached as appropriate.

The applicable Product Assurance requirements are provided in the “General Design and Interface Requirements” AD01 (design requirements) and in the “PA Requirements for Subcontractors” AD08 (product assurance general; quality assurance; dependability; safety including product liability; EEE-parts with special chapter on radiation hardness assurance; parts, materials and processes; cleanliness & contamination control; deliverable PA documentation, …).

The applicable Software Product Assurance requirements are provided in “SW PA Requirements for Subcontractors” AD07 (including requirements for SW PA on firmware resident in PROM and ASICs or FPGAs; boot & init SW, etc).

5.1 Failure Tolerance

The failure tolerance requirements of GDIR [AD01] apply as listed in the GDIR applicability matrix provided in Section 8. The GDIR requirements GDI-3136, GDI-3119, GDI-3123 cannot be used on equipment level and they are applicable as derived below:

SEPS-5970//A

The design of units with embedded redundancy shall be such that a single component/part failure (e.g. resistor, transistor) cannot, as far as practicable, cause the failure of any function of the equipment.

Single point failures which cannot be eliminated from the design with reasonable effort (or fault tolerance requirements which cannot be met) shall be summarised in a Single Point Failure/Critical Items List. They are subject to formal approval by the customer up to prime Contractor on a case by case basis with a detailed retention rationale.

SEPS-5971//A

The Contractor shall verify the capability of the design to sustain single failure as defined by the following failure tolerance requirement:

• No single hardware failure or operator error shall cause effects on equipment functions of the dependability severity category 1 (Propagation of failure to other subsystem/ assembly/ equipment) and - for units with embedded redundancy only - level 2 (Loss of functionality). Single point failures which cannot be eliminated from the design with reasonable effort (or fault tolerance requirements which cannot be met) shall be summarized in a Single Point Failure/Critical Item List. They are subject to formal approval by the customer up to prime Contractor on a case-by-case basis with a detailed retention rationale.

Prime Contractor will decide whether dedicated ESA system level requirements are violated and forward the approval requests to ESA as necessary.

SEPS-5973//A

Any command or command sequence that can cause

• consequences of the hazard severity category 1 (Catastrophic - Loss of human life; life threatening, permanently disabling injury or occupational illness) or

• dependability severity category 1 (Propagation of failure to other subsystem/ assembly/ equipment) or

• - for units with embedded redundancy only - level 2 (Loss of functionality) or


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• cause damage to flight hardware if issued inadvertently or not issued when required (out of sequence commanding)

shall be identified in the FMECA and reported in the Hazard Analysis.


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6 VERIFICATION AND TEST REQUIREMENTS

6.1 General requirements

SEPS-856//R

The Contractor shall meet the following verification and test requirements as a minimum. However, these requirements should not necessarily be considered as exhaustive, and the Contractor shall also include additional tests as necessary to demonstrate complete compliance of the SEPS with the requirements above.

6.1.1 Responsibility for Inspection and Test

SEPS-476//R,TBC

Unless otherwise specified in the contract or Statement of Work (SOW), the Contractor is responsible for the performance of all inspection and test requirements as specified herein.

6.1.2 Quality Assurance Programme

SEPS-478//R

The Contractor shall have or shall establish and implement a Quality Programme that complies with the requirements of Section 5.

6.1.3 Surveillance, and Witness of Inspection and Test

SEPS-480//I,R

The Customer shall be given access to the Contractor's facilities at all times in order to inspect the Contractor's quality control system and the records specified to be maintained therein. The Contractor shall ensure that appropriate arrangements are made for access to lower tier contractors' facilities/test houses where relevant processes are to be performed.

SEPS-481//I,R

The Customer (or their nominated representatives) reserve the right to witness, perform, or review the tests or documentation of any of the inspections set forth in the specification where such inspections are deemed necessary to assure that supplies and services conform to prescribed requirements.

SEPS-482//R

The Contractor shall notify the Customer at least 2 weeks and subsequently 48 hours prior to the commencement of the qualification or acceptance test phases to enable representation by the Customer and witnessing of any or all tests as considered necessary by the Customer.

6.1.4 Preproduction Sample

SEPS-484//I,R

Prior to manufacturing of a new equipment batch, the Contractor shall verify the use of the same materials, techniques and processes as are applicable to the units referred to Section 6.2.3.2.

6.1.5 Classification of Inspection and Test

SEPS-486//R

The examination and testing of the SEPS and its equipments shall be classified as follows:

• Qualification Inspection and Testing (Section 6.2.3.3)

• Acceptance Inspection and Test (Section 6.2.2.2)

• Preparation for delivery Inspection and Test (Section 6.5)


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6.1.6 Thruster Firing Tests

SEPS-849//R

For all qualification, acceptance and life tests which involve firing of the thruster, the following requirements shall apply.

SEPS-850//I,R

The test facility shall not introduce any effects which shall lead to test results which would deviate from those achieved in orbit, or degradation of the SEPS to any extent beyond that which would be experienced in orbit.

SEPS-851//A,R

For specific instances where compliance with SEPS-850 is deemed to be impossible, these shall be submitted to the Customer for approval. This submission shall be fully justified, and all deviations between ground test results and in-orbit behaviour analysed and quantified.

SEPS-857//T

All firing tests shall include direct thrust and flow rate measurement.

SEPS-858//T,A,I,R

The Contractor may propose alternative methods for thrust and flow rate determination during the life test, if direct measurement is deemed to be impractical. Any such alternatives are subject to Customer approval. They shall be fully justified, with deviations between the proposed method and direct measurement analysed and quantified, and shall include the provision for periodic calibration checks of the proposed method (frequency to be agreed between the Contractor and Customer).

SEPS-852//T,R

The qualification firing tests shall include full simulation of the thermal impacts corresponding to the solar illumination conditions identified in SEPS-181 and SEPS-182, with the thruster operating at full power. This test shall include all parts of the SEPS which are affected by this thermal load.

SEPS-990//T,R

The above thruster verification test shall include firing under the maximum temperatures expected during the mission, while in the flight configuration. The temperature reached on the thruster during the testing shall be sufficient to cover all contributions from the thermal interactions which will occur when installed on the spacecraft. The testing shall be of sufficient duration to ensure that equilibrium temperatures are reached on all parts of the tested system. If using infra-red simulation of the in-flight solar fluxes, account shall be made for the differences between the amounts of infra-red and ultra-violet flux that will be absorbed by the thrusters and the spacecraft.

SEPS-5331//A,R

Thruster life and acceptance tests shall take into account impacts of the test facility on thruster operations and performance including but not limited to background pressure effects, deposition of sputter material onto the thruster.

SEPS-5332//R

The qualification thruster shall be exposed to acceptance tests, and multiple air exposures after firing, prior to start of life test - also including margin for possible re-acceptance of flight units. This is to simulate the normal processes a flight thruster is exposed to before flight.

The SEPS shall be characterised it determine its performance over the extended voltage operating range at BOL and EOL as defined in SEPS-4836.


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6.2 Verification of Compliance

SEPS-488//T,A,I

Compliance with the requirements of Section 3 shall be verified by acceptance inspections and tests, qualification, or analysis.

SEPS-489//I,R

The method of verification of all paras of Section 2, Section 3 and Section 6 of this specification shall be presented in a Design Verification Matrix Report in a format defined by the Customer in the Statement of Work.

6.2.1 General

6.2.1.1 Acceptance Inspections and Tests

SEPS-494//T,I

The applicable paragraphs of Section 3 shall be verified by performing acceptance inspections and tests in accordance with Section 6.2.2 on each deliverable SEPS and its equipments.

6.2.1.2 Qualification

SEPS-496//T,I

Qualification of the SEPS to meet the requirements of Section 3 may be demonstrated as specified below. A combination of the following methods may be used to demonstrate qualification, subject to Customer approval.

SEPS-497//R

Qualification Inspection and Tests

Design Verification of the SEPS shall be established by performing the qualification inspections and tests detailed in Section 6.2.3. The SEPS hardware used for these tests shall not subsequently be used for the flight spacecraft.

SEPS-498//R

Qualification by Similarity

If the Contractor can demonstrate by analysis that the proposed equipment is similar in design, construction and performance to existing space qualified equipment and that previous qualification covers all or part of the performance and environmental requirements of Section 3, then the Contractor may offer "Qualification by Similarity" against the relevant requirements, qualification testing may be then omitted subject to Customer approval.

SEPS-499//R

Qualification by Analysis

Where analysis is proposed to demonstrate compliance with any of the requirements of this specification, it is subject to Customer approval.

6.2.2 Acceptance Inspection and Test

6.2.2.1 Test Sample

SEPS-502//R

All deliverable SEPS units produced in accordance with this specification, shall be subjected to the acceptance tests specified in Section 6.2.2.2.

SEPS-503//I

Each unit shall be clean prior to entering acceptance testing in accordance with Section 6.4.11


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6.2.2.2 Acceptance Tests Required (Minimum)

SEPS-505//R

Acceptance inspection and tests shall be conducted in the following sequence, unless otherwise agreed by the Customer:

SEPS-915//T,I,R

Unit level SEPS Paragraph

SEPT FCU PPU Pipework Harness Level Number

Inspection & Mass x x x x Section 6.4.1

Proof pressure test 1 x x Section 6.4.2

Leakage 1 x x Section 6.4.3

Functional x x x x 6 Section 6.4.5

Performance 3 x x x 6 Section 6.4.6

Resonant search x x x x x Section 6.4.7.1

Random vibration x x x x x Section 6.4.7.2


Sine vibration x x x x x Section 6.4.7.3


Constant acceleration

4 4 4 x x Section 6.4.8




Thermal vacuum 2 x x x 5 2 Section 6.4.9


Functional x x x x 6 x Section 6.4.5

Performance 3 x x x 6 x Section 6.4.6

Cleanliness x x x Section 6.4.11

Final inspection x x x x x Section 6.4.1

SEPS-916//T,I,R

Notes (see item numbers above):

1. Proof and leakage tests for the thruster are TBC

2. Thermal vacuum tests for the SEPT are to be performed at thruster or SEPS level

3. Performance tests for the SEPT are to performed at SEPS level (at least); additional tests at SEPT level may be proposed by the Contractor

4. May be deleted for acceptance test

5. Thermal Vacuum tesing of the Pipework & Harness shall be done in conjunction with the TPM - TBC


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6. Certain Performance testing of the Pipework & Harness e.g accomodation of the of the angular slews of the TPM, shall be done in conjunction with the TPM -TBC

6.2.2.3 Failure Criteria

SEPS-552//T

The SEPS units shall exhibit no failure, malfunction or out-of-tolerance performance degradation as a result of acceptance inspections and tests specified in Section 6.2.2.2. Any such occurrence shall be cause for rejection.

6.2.2.4 Test Limitations

SEPS-556//A,R

The Acceptance Inspection and Test shall not degrade the SEPS performance or expose the units to test levels or conditions which could induce a subsequent failure.

6.2.2.5 Rejection and Re-Submittal

SEPS-558//I

Any failure, malfunction or out-of-specification conditions which occur during the test programmes shall result in immediate stoppage of the test to avoid the possibility of further hazard to equipment or personnel. Testing shall not be recommenced unless the condition has been properly investigated and the proposed recovery and corrective action has been reviewed and approved by the Customer. In the case of a failure requiring replacement or rework, the test programme shall be repeated in its entirety except as mutually agreed between the Contractor and the Customer.

6.2.3 Qualification Inspection and Test

6.2.3.1 SEPS Life Verification


The total impulse, operational time, and cycling requirements shall be demonstrated by means of a life test, which shall include the thruster, FCU and PPU supplies at EQM or QM level; the life test profile, taking into account the thrust level throttling requirements, shall be subject to Customer approval. Note that nominal proposed life test profiles are provided below. It shall also be possible for the Customer to introduce active elements of the Xenon feed system (e.g. pressure regulator) into this life test (in full or in part).

SEPS-71/MPB-3689/

During thruster qualification testing, a beam-out counter system shall be used.

SEPS-72//T,A

The SEPS performance shall be measured throughout the life test in accordance with Section 6.4.6. The Contractor shall analyse performance trends based on these measurements. If these trends indicate that the performance may violate the specification requirements at any future point in the SEPS life, or lead to deviations from the performance models (see Section 3.3.5) outside the scope of the error bounds declared therein, this shall be notified to the Customer with immediate effect. In this event, the Customer may declare a test failure, and the requirements of Section 6.2.3.6 shall then apply.

SEPS-2569//T

The life test shall be conducted in accordance with thrust profile defined in SEPS-2570 below (TBC) This is based on the flight profile ref. SEPS-67


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Thrust (mN) Cycle #

Start End No repeats Duration per

repeat (hours) Impulse (Ns)

Constant thrust: 1 90 90 2 300.00 1.94E+05 2 100 100 2 150.00 1.08E+05 3 120 120 2 1.00 8.64E+02 4 125 125 2 1.00 9.00E+02 5 130 130 2 1.00 9.36E+02 6 135 135 2 1.00 9.72E+02 7 145 145 10 1000.00 5.22E+06 8 145 145 3 2000.00 3.13E+06

Ramp up: 9 90 100 2 200.00 1.37E+05 10 125 145 2 200.00 1.94E+05 11 140 145 2 500.00 5.13E+05

Ramp down: 12 100 90 2 250.00 1.71E+05 13 105 100 2 400.00 2.95E+05 14 145 130 2 500.00 4.95E+05

Totals: 37 21008.00 1.05E+07 Total duration (excl. off time and facility down time): 2.40 years

Note 1: thrust ramp up and ramp down cycles should ideally vary the thrust level linearly with time; discrete changes on a daily basis to achieve a close equivalent profile are considered acceptable, provided the total impulse and total firing times are conserved. Note 2: Additional cycles will be required to demonstrate compliance with the requirements of SEPS-68.

SEPS-930//R

The Contractor shall submit and implement a test plan for the life verification of the neutraliser, taking into account the enhanced operating current requirement to support operation of 2 thrusters simultaneously (see SEPS-929)

SEPS-4823//T

During life test, simulated High Pressure Regulator (HPR) pressure cycles of representative frequency (TBD) and pressure range (ref. SEPS-80 and SEPS-81), shall be used to feed xenon to the FCU.

SEPS-202/MPB-3691/T

Full qualification tests shall be applied to the harness including thermal testing while operational

6.2.3.2 Test Sample

SEPS-561//I,R

Prior to the commencement of qualification testing, sufficient testing shall have been performed on representative development units to give both the Contractor and the Customer confidence to proceed. This shall be specified in the Contractor’s Development Test Plan.

SEPS-562//I,R

Qualification testing shall be carried out on flight standard units which have been manufactured in accordance with the requirements of this specification. The units shall be identical to the units that shall be supplied for flight spacecraft.

SEPS-564//T,I,R

The units shall complete acceptance testing (less acceptance random vibration) to Section 6.2.2 and then shall be subjected to all the qualification tests specified in SEPS-568.

SEPS-565//T

For all pressurised items requiring demonstration of the burst pressure requirements as identified in Section 4.1.1.2.

SEPS-566//

All non-flight units shall be identified “NOT FOR FLIGHT USE”.


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6.2.3.3 Qualification Tests Required

SEPS-568//I,R

As a minimum, the qualification inspection and tests shall be conducted in the following sequence, unless otherwise agreed by the Customer:

SEPS-569//T,I,R

Unit level SEPS Paragraph

SEPT FCU PPU Pipework Harness Level Number

Inspection & Mass x x x x x Section 6.4.1

Proof pressure test 1 x x Section 6.4.2





Random vibration x x x x x Section 6.4.7.2


Sine vibration x x x x x Section 6.4.7.3


Constant acceleration 3 3 3 x x Section 6.4.8




Thermal vacuum 2 x x x x x Section 6.4.9


Functional x x x x 7 x Section 6.4.5

Performance 4 x x x 7 x Section 6.4.6

EMC x x x x x Section 6.4.10

Cleanliness x x x Section 6.4.11

Final inspection x x x x x Section 6.4.1

Life Test 5 5 5 6 6 x Section 6.2.3.1

Burst x x x Section 6.4.4

Final Inspection x x x x Section 6.4.1

SEPS-924//T,I,R

Notes (see item numbers above):

1. Proof and leakage tests for the thruster are TBC

2. Thermal vacuum tests for the SEPT shall be performed at thruster or SEPS level

3. Constant acceleration may be verified by sine dwell if requested by the Contractor; this approach has to be justified by the Contractor, and is subject to formal approval by the Customer


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4. Performance tests for the SEPT shall be performed at SEPS level (at least); additional tests at SEPT level may be proposed by the Contractor.

5. The life test shall be performed at SEPS level as identified in Section 6.2.3.1 above; any additional life testing requirements which are not covered by this test shall be identified and performed by the Contractor.

6. Life testing of the Pipework & Harness shall be done in conjunction with the TPM - TBC

7. Certain Performance/Functional testing of the Pipework & Harness e.g accomodation of the of the angular slews of the TPM, shall be done in conjunction with the TPM -TBC

6.2.3.4 Failure Criteria

SEPS-654//T,I

The SEPS and its units shall exhibit no failure, malfunction or out of tolerance performance degradation as a result of Qualification inspections and tests specified in Section 6.2.3.3. Any such occurrence shall be cause for rejection and refusal to grant qualification

6.2.3.5 Qualification Tests Report

SEPS-656//A,R

Following the completion of qualification tests, a test report containing the test results, together with an evaluation and comparison with the requirements, shall be delivered in accordance with the SOW.

6.2.3.6 Rejection and Re-Submittal

SEPS-658//I,R

Any failure, malfunction or out-of-specification conditions which occur during the test programmes shall result in immediate stoppage of the test to avoid the possibility of further hazard to equipment or personnel. Testing shall not be recommenced unless the condition has been properly investigated and the proposed recovery and corrective action has been reviewed and approved by the Customer. In the case of a failure requiring replacement or rework, the test programme shall be repeated in its entirety except as mutually agreed between the Contractor and the Customer.

6.3 Test Conditions and Test Equipment

6.3.1 Ambient Conditions

SEPS-661//I

Unless otherwise specified herein, all measurements and tests shall be made within the following ambient conditions:

1 Temperature 23°C ± 5°C

2 Relative Humidity 60% maximum

3 Pressure 760 ± 25 mm mercury

SEPS-662//I

All pressures and temperatures shall be recorded unless specified otherwise.

SEPS-663//I

Whenever these conditions shall be closely controlled in order to obtain reproducible results, a reference temperature of 23°C, a relative humidity of 50% and an atmospheric pressure of 760 mm of mercury respectively shall be used, together with whatever tolerances are required to obtain the desired precision of measurement.


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SEPS-664//I

Test facilities with uncontrolled environments may be used with Customer approval, provided that:

• The conditions shall not adversely affect the unit performance

• The conditions shall not compromise the internal cleanliness of the unit.

6.3.2 Test Equipment

SEPS-666//I

The apparatus used in conducting tests shall be capable of producing and maintaining the required test conditions as defined in the applicable test procedures.

6.3.3 Tolerance of Test Conditions (Excluding Ambient)

SEPS-670//I

The maximum allowable tolerances of test conditions (inclusive of accuracy of instruments) shall be as follows unless otherwise stated in this specification.

a) Temperature: max temp. -0°C +3°C

min temp. +0°C -3°C

b) Pressure: General +5%, -0

When devices are used such as ion gauges, whose accuracy depends on location and type of gauge and which, therefore, can only be specified in test procedures, the actual achieved pressure must be equal to or lower than that specified.

c) Relative humidity: ± 5%

d) Acceleration: +10%, -0

e) Vibration level: sinusoidal +10%, -0% “g” peak.

(Random) power spectral density 90 - 700 Hz +2, -1 dB

otherwise ± 3dB

(Random) overall acceleration (rms) +10%, -0

Lower is acceptable only if as result of an agreed notching policy

f) Frequencies: ± 2% ± 0.5 Hz below 20 Hz.

g) Time: +5%, -0%

h) Acoustic pressure: +/-3, -0 dB in each octave band

+2, -0 dB for OASPL

i) Force (static tests): -0, +5%

j) Dry mass: ± 5 gram


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k) Shock test tolerance: From 100 Hz up to 1kHz: +0/+3 dB

From 1 kHz up to 10kHz: +0/+6 dB

l) Volume measurement ± 0.2 litres

6.3.4 Accuracy of Measurement

SEPS-672//I,R

The accuracy of all instruments and test equipments used to control or monitor the test parameters, whether located at the Contractor's testing laboratory or at a Contractor's plant shall be verified by calibration. The calibration period shall be defined by the equipment manufactures handbook.

6.3.5 Test Media

SEPS-674//I,R

Helium gas (to AD11)

Xenon gas (to AD13)

Nitrogen gas (to AD12)

Isopropyl Alcohol (to AD14)

Use of other test media are subject to approval by the Customer.

6.3.6 Product Test Controls

SEPS-676//R

Controls for item configuration, testing item documentation, non-conformance and failure reporting, the Customer and the Customer's Customer inspection and test surveillance shall be as specified in Section 5.

6.4 Test Methods

SEPS-678//R

The following tests shall be carried out in the sequence specified in Section 6.2.2.2 and Section 6.2.3.3.

6.4.1 Inspection/Examination

SEPS-680//I

The unit shall be inspected by Contractor Quality Assurance for the applicable requirements listed below in accordance with this specification and approved Contractor standards. Mechanical inspection criteria shall be as specified on the applicable drawings.

6.4.1.1 Dimensions

SEPS-682//I,R

The unit shall be measured for compliance with the overall dimensions and mounting requirements of the unit ICD.

6.4.1.2 Identification and Marking

SEPS-686//I

The unit shall be inspected for compliance with the marking requirements AD01 section GDI-86


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6.4.1.3 Materials and Processes

SEPS-688//I

The unit shall be visually inspected and manufacturing records and drawings shall be reviewed to verify that materials and processes used conform to specified requirements. Inspection shall verify the following as a minimum:

• Completeness of product.

• Conformance to drawings or other manufacturing documents

• Completion of all steps in the manufacturing process and proper certification.

• Workmanship, assembly and fit.

• Materials, parts and finish.

• Welds shall have been inspected during build by the Customer approved method of Non-Destructive Inspection (NDI) such as X-ray, ultrasonic, eddy current or a combination of these methods.

• There shall be no evidence of nicks, scratches, cracks, impacts, burrs or any defect (or physical imperfection) which would adversely affect the unit's performance or compromise cleanliness.

6.4.1.4 Physical Measurements

SEPS-690//T,I

The following physical measurement shall be performed:

• The mass of each unit shall be measured.

• The centre of gravity shall be measured.

6.4.2 Proof Pressure Test

SEPS-692//T

All pressurised units shall be subjected to one pressure cycle to the proof pressure specified by Section 4.1.1.1. This pressure level is to be applied above ambient pressure. The time at proof pressure shall be not less than 7½ minutes. The proof test shall be performed with an inert test gas which has been demonstrated to be compatible with the SEPS.

SEPS-693//I

Unit dimensions before, during and after proof testing shall conform to those specified in the unit ICD. Evidence of permanent set greater than 0.2 per cent shall be cause for rejection.

SEPS-694//T

The above proof pressure test shall be carried out at the worst temperature case (acceptance or qualification level as applicable) specified in SEPS-287.

SEPS-695//T,A

Subject to Customer approval the Contractor may test at ambient temperature if the test pressure is factored up to give the equivalent worst case qualification thermal load conditions, (or analysis is supplied to establish that the thermal conditions do not adversely affect the equipment or its performance).


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6.4.3 Leakage Tests

SEPS-725//T

Each pressurised SEPS unit shall be subjected to helium leak test at MEOP.

SEPS-726//T

The internal and external leakages shall not exceed the limits specified in Section 3.2.2.

6.4.4 Burst Test

SEPS-5326//T

Each pressurised SEPS unit shall be subjected to a burst test.

SEPS-752//T

The Contractor shall obtain the Customer permission before commencing burst test.

SEPS-753//T

The unit shall be subjected to the burst pressure specified in Section 4.1.1.2. This pressure level is to be applied above ambient pressure

SEPS-754//T

The above pressure shall be applied at a uniform rate and the required pressure shall be reached in not less than 20 seconds.

SEPS-755//T

Once burst pressure is reached the pressurisation shall continue until the unit ruptures.

SEPS-756//T

The above burst pressure shall be carried out at maximum temperature (acceptance or qualification level as applicable) specified in SEPS-287.

SEPS-757//T,A

Subject to the Customer approval, the Contractor may test at ambient temperature if the test pressure is factored up to give the equivalent worst case qualification thermal load conditions (or analysis is supplied to establish that the thermal conditions do not adversely affect the equipment or its performance).

SEPS-758//I

The unit shall not rupture at or below the specified burst pressure level.

SEPS-759//A,I

Following rupture the unit shall be subject to laboratory examination to confirm the failure modes.

6.4.5 Functional Tests

SEPS-894//T

Each of the SEPS equipments shall be subject to the following functional tests.

6.4.5.1 Thruster

SEPS-896//T

The thruster functional tests shall include at least:

• Electrical resistance measurements

• Electrical continuity checks

• Electrical insulation/isolation measurements

• Electrical ground bonding checks


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• Grid alignment checks

6.4.5.2 FCU

SEPS-898//T

The FCU functional tests shall include at least:




• Valve response

• Flow rate measurement

• Leakage - both internal and external

6.4.5.3 PPU

SEPS-900//T

The PPU functional tests shall include at least:




• TM/TC interfaces

• Operational modes

• Operation of all supplies within the PPU

• Verification of internal FDIR functions

6.4.5.4 Pipework And Harness

SEPS-4919//T

The Pipework and Harness functional tests shall include at least:



• Electrical ground bonding checks

• Deflection accommodation test

• External leakage test

6.4.5.5 SEPS

SEPS-908//T

The functional test to be performed at SEPS level shall include, but shall not be limited to:

• Correct connection between SEPS units

• Correct operation of the thruster and FCU when stimulated by the corresponding commands through the PPU


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6.4.6 Performance Tests

6.4.6.1 Thruster

SEPS-903//T

The thruster performance tests shall include at least:

• Thrust measurement

• Specific impulse measurement

• Electrical measurements (voltages, currents, power)

• Thrust vector measurement

SEPS-906//T

The thruster performance test shall be performed at SEPS level (at least); it may also be performed at thruster level if deemed necessary by the contractor

SEPS-911//T

The above thruster performance measurements shall be performed to encompass the complete SEPS operating range identified in this document. The set points for these tests are to be agreed by the Contractor and Customer prior to TRR.

6.4.6.2 FCU

SEPS-905//T

Additional tests (in addition to those performed for the functional tests) to verify correct performance of the FCU may be performed as proposed by the contractor. These tests are to be agreed by the Customer prior to TRR.

6.4.6.3 PPU

SEPS-910//T

The PPU performance tests shall include operation of the PPU up to full power. The performance of each of the PPU supplies shall be verified, and the input current and power measured.

6.4.6.4 SEPS

SEPS-914//T

The SEPS performance tests shall verify the above performance parameters, with the elements of the SEPS connected together in a flight representative configuration.

6.4.7 Vibration Tests

6.4.7.1 General Requirements

SEPS-698//T

A sine vibration survey of 0.5 g, 10 to 2000 Hz shall be conducted in each of the three mutually perpendicular axes prior to and after performing the qualification and acceptance tests specified.

SEPS-699//T

Survey results shall indicate no unreasonable shift between pre and post vibration surveys attributable to a change in test item or test fixture characteristics.

SEPS-700//T

Each of the SEPS units shall meet the relevant stiffness requirement detailed in Section 4.3.3.

SEPS-701//T

The transmissibility and cross-talk of the test fixture shall be determined by a swept sine vibration (as above) or a low level random vibration applied in each of three mutually perpendicular axes.


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SEPS-702//T

The test fixture shall be sufficiently stiff to be considered rigid for the frequency range up to 2000 Hz (random case) and 100 Hz (sine case).

SEPS-703//I

The axis definition for each SEPS equipment shall be as specified on its ICD.

SEPS-704//I

The equipment shall be mounted to a test fixture simulating the mechanical mounting interface with the spacecraft.

SEPS-705//T,A

The vibration spectrum as defined in Section 6.4.7.2 and Section 6.4.7.3 may, with written approval (via RFD) from the Customer, be notched if necessary due to test fixture limitations/resonances. The notching policy shall be agreed with the Customer prior to the QTRR.

SEPS-707//T

For qualification, the vibration test shall be performed with pressurised units subjected to their relevant MEOP

SEPS-708//T

The internal leak rate shall be measured during vibration tests of the FCU. The measured leak rate shall not exceed that specified in SEPS-19.

SEPS-710//T,A

If the two lateral axes can be shown by symmetry to sustain identical loads, then one lateral axis may be used for qualification vibration. The different test cases shall use different lateral axes.

SEPS-711//T

The testing or analysis shall also demonstrate that the unit meets the stiffness requirement (Section 4.3.3).

SEPS-713//T

For each unit which is exposed to flight propellants, cleanliness verification in accordance with Section 6.4.11 shall be performed prior to and immediately after the qualification and acceptance vibration testing.

6.4.7.2 Random Vibration

SEPS-715//T

Observing the general requirements of Section 6.4.7.1, the SEPS units shall be subjected to random vibration inputs separately along the three orthogonal axes at the following levels.

SEPS-716//T

• Qualification

180 seconds per axis at Qualification Levels defined in SEPS-281 or SEPS-282, as required for the unit under test.

SEPS-717//T

• Acceptance

60 seconds per all three axes at Acceptance Levels defined in SEPS-425, as required for the unit under test.

SEPS-718//I

Following testing, the unit shall be inspected to confirm no physical damage.


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6.4.7.3 Sinusoidal Vibration Test

SEPS-720//T

Observing the general requirements of Section 6.4.7.1, the SEPS units shall be vibrated at the levels specified in Section 4.2.2.2 and Section 4.2.2.1.1.

SEPS-721//T

The levels shall be measured at the C of G of the unit.

SEPS-722//T

The levels shall be applied along each of three orthogonal axes at a sweep rate as defined in Section 4.2.2.1.1.

SEPS-723//I

Following testing the unit shall be inspected to confirm no physical damage.

6.4.8 Constant Acceleration

SEPS-761//T

The unit shall be subject to the constant acceleration levels specified in SEPS-422, applied in the three orthogonal axes as defined in the unit ICD.

SEPS-762//T

The differing acceleration levels imposed by the centrifuge (if used ) across the unit being tested shall not vary from the specified acceleration by more than ± 10 per cent.

SEPS-763//T

The acceleration specified shall be applied at the location of the centre of gravity of the unit.

SEPS-764//T

The minimum duration of the test shall be 15 seconds for each acceleration direction.

SEPS-765//T

During the test the unit shall be mounted in a test fixture simulating the mechanical mounting interface with the spacecraft and pressurised to its relevant MEOP..

SEPS-766//I

The unit shall be inspected after each test for evidence of physical damage.

SEPS-768//T

The internal leak rate shall be measured during acceleration tests of the FCU. The measured leak rate shall not exceed that specified in SEPS-19.

6.4.9 Thermal Vacuum Tests

SEPS-773//I,R

The unit shall be tested in a thermal vacuum environment having a pressure of 1 × 10-5 torr or less.

SEPS-5327//I

For the PPU equipments the Unit shall be mounted on a representative baseplate, which represents the local cooling effects of the heatpipe configuration of the flight platform, in order to validate the thermal modeling.

SEPS-775//T

For the FCU equipment level test, the vacuum may be omitted if it can be shown that it has no adverse effects on the equipment or its subsequent performance, which is then subject to Customer approval


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SEPS-772//T

The unit shall be subjected to hot and cold cycles, to the levels specified in SEPS-5991.

SEPS-918//T

The performance of the unit shall be verified in accordance with Section 6.4.6 at each of the temperature extremes.

SEPS-921//T

For the FCU, the internal leakage shall be verified at each of the temperature extremes.

SEPS-917//I

The unit shall be inspected after the test to confirm no physical damage has occurred as a result of the test.

SEPS-919//T

For the SEPS level thermal vacuum test, the following SEPS-920 and SEPS-922 shall apply:

SEPS-920//T

The thruster shall be subjected to thermal vacuum environment as specified above

SEPS-922//T

The vacuum level shall be sufficient to ensure compliance with Section 6.1.6, with the thrusters firing at any point within the range specified in this document

6.4.10 EMC Tests

SEPS-925//T

The Contractor shall submit a EMC plan for the verification of the requirements AD 03

SEPS-926//T,A

These analyses and tests identified in this plan shall be performed by the Contractor following Customer approval.

SEPS-927//T

The above verification activities shall encompass all EMC aspects identified in AD 03.

6.4.11 Cleanliness Verification

6.4.11.1 Qualification Cleanliness

SEPS-736//T

The purpose of this test is to verify that the unit still meets the cleanliness requirements of Section 4.1.5.1.7 after completing any preceding tests.

SEPS-737//T

The unit should be clean prior to entering qualification testing.

SEPS-738//

It should not be subjected to any cleaning procedure immediately prior to this Cleanliness Verification (except at test sequence step 4) or after any preceding tests (unless otherwise stated).

SEPS-739//

The unit shall be flushed with the specified quantity of Isopropyl Alcohol to AD14.

SEPS-740//

A 100 ml fluid sample, or 100 ml of fluid per 929 cm2 (1 ft2) of internal surface area, whichever is the greater, shall be used. The effluent shall be withdrawn from the unit for particle count and NVR assessment.


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SEPS-741//

The particulate count of the total effluent sample when tested using a procedure approved by Astrium Satellites, shall meet the requirements of Section 4.1.5.1.7._

SEPS-742//I,R

In the event that the equipment fails to meet the specified requirement on the first cleanliness verification test, the Contractor shall inform the Customer of the failure and particulate count, and await the Customer approval before subjecting the equipment to additional cleaning, cleaning verification tests or any other tests.

SEPS-743/MPB-4548/T

Following the cleanliness verification test, the unit shall be gas purged and thoroughly dried in vacuum to a Customer approved procedure to remove all traces of residual liquid.

SEPS-744//I

The unit shall then be protected against contamination in accordance with Section 4.1.5.1.7 prior to removal from the contamination controlled area.

6.4.11.2 Acceptance Cleanliness

SEPS-747//T

The unit shall meet the requirements specified in Section 4.1.5.1.7. Final cleaning is to be performed with IPA.

SEPS-748/MPB-4548/T

Following the cleanliness verification test, the unit shall be gas purged and thoroughly dried to a Customer approved procedure to remove all traces of residual liquid.

SEPS-749//T

The dryness shall be verified to meet the requirement of Section 4.1.5.1.7.

SEPS-750//I,R

The unit shall then be protected against contamination in accordance with Section 4.1.5.1.7 prior to removal from the contamination controlled area.

6.4.12 Visual Inspection

SEPS-831//I

The unit shall be subject to inspection to ensure no damage.

6.4.13 Preparation for Data Review

SEPS-833//A,I

The unit shall be inspected following the testing for physical damage by Contractor quality assurance. Data taken during testing shall be compiled, required analysis and computations shall be performed and all test data shall be reviewed and certified by Contractor quality assurance. The quality data shall then be submitted to the designated the Customer representative for the review and approval as defined in the Statement of Work.

6.4.14 Shock Test

SEPS-837//T

The unit shall be subjected to the shock spectrum identified in SEPS-434 (thruster) or SEPS-TBD other units.

SEPS-838//A,R

The shock input to the unit may be omitted if shown by analysis that it is already enveloped by other test requirements:


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SEPS-840//T

The response spectrum levels shall be applied in each of the three orthogonal axes.

6.5 Preparation for Delivery, Inspection and Test

SEPS-842//I

Examination of preservation, packaging, and marking shall be conducted to assure compliance with the requirements of SEPS-3674 of this specification.

6.6 Documentation

The documentation requirements are fully specified and defined in AD08.


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7 ABBREVIATIONS LIST

1553B MIL-STD-1553B conform communication interface

A Analysis

AIT Assembly, Integration & Test

ATP Authorisation to Proceed

BER Bit Error Rate

CoG Centre of Gravity

D Definition

DOR Differential Offset Ranging

EFM Electrical Functional Model

EMC Electromagnetic Compatibility

ESA European Space Agency

FCU Flow Control Unit

GDIR General Design and Interface Requirements Specification

I Inspection

ICD Interface Control Document

Id Identifier

PM Phase Modulation

PPU Power Processing Unit

PSK Phase Shift Keying

R Review of Design

RF Radio Frequency

RNG Ranging

RX Receiver

S Similarity

S/C Spacecraft

SDS Satellite Design Specification

SEPS Solar Electric Propulsion System

SEPT Solar Electric Propulsion Thruster

T Test

TBC To Be Confirmed

TBD To Be Defined

TBW To Be Written

TC Telecommand

TM Telemetry

TT&C Tracking, Telemetry & Command

TX Transmitter

VSWR Voltage Standing Wave Ratio


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8 GDIR APPLICABILITY MATRIX

The following table lists the applicable requirements of the GDIR.

It contains, in the first column, the Local ID for each applicable GDIR requirement number.

The second column contains the GDIR Requirement number and the opening text of the requirement.

The third column defines the Applicability Y/N

The final column shows the intended verification method. If no method is shown it shall be assumed that verification is required and the method is TBD

Req No. Reference Applicability Verif. Method

2.1 Applicable Documents SEPS-4975 GDI-3994:

The following documents, of the latest issue, or o ... Y

2.2 Applicable Standards SEPS-4976 GDI-3993:

The following documents, of the latest issue, or o ... Y

2.2.1 ECSS 2.2.2 Military/Industrial 3.1.1 Lifetime SEPS-3647 GDI-35:

The equipment/subsystem shall meet the requirement ... Y TBD

SEPS-3648 GDI-38: Maintenance during storage shall be as limited as ...

Y A

SEPS-3649 GDI-53: The MTM equipment/subsystems shall be designed wit ...

Y T,A

SEPS-3650 GDI-48: Where the design margin on nominal lifetime is not ...

Y R,TBC

SEPS-3651 GDI-49: The lifetime of items which degrade shall be desig ...

Y R,TBC

3.1.2 Safety and Product Liability SEPS-3653 GDI-55:

The subcontractor shall comply to the applicable s ... Y A

SEPS-3654 GDI-56: The subcontractor shall comply to the applicable p ...

Y A

SEPS-4977 GDI-3136: The design of the ASP, MPB and ETA subsystems shal ...

Y A

SEPS-4978 GDI-3137: Alternate or redundant paths shall be functionally ...

Y A

SEPS-4979 GDI-3138: Checkout of all redundant paths and contingency op ...

Y A

SEPS-4980 GDI-3118: The contractor shall verify the capability of the ...

Y A

SEPS-4981 GDI-3119: No single hardware failure or operator error shall ...

Y A

SEPS-4982 GDI-3120: No single hardware failure or operator error shall ...

Y A

SEPS-4983 GDI-3121: No two hardware failures, two operator errors, a c ...

Y A

SEPS-4984 GDI-3122: Improper command or command sequences or software ...

Y A

SEPS-4985 GDI-3123: Any command or command sequence that can cause con ...

Y A

SEPS-4986 GDI-3163: Error protection and detection shall be by single ...

Y R


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SEPS-4987 GDI-3164: There shall be redundant non-volatile memory avail ...

Y R

SEPS-4988 GDI-3165: Non-volatile reprogrammable memory shall be availa ...

Y R

SEPS-4989 GDI-3170: In the case of multiple read errors at the same lo ...

Y R

SEPS-4990 GDI-3171: The total number of errors shall be available in t ...

Y R

SEPS-4991 GDI-3172: The volatile memory shall be protected by an Error ...

Y R

SEPS-4992 GDI-3173: Each processing unit shall count the single bit co ...

Y R

SEPS-4993 GDI-3174: The memory allocated to one processor shall not be ...

Y R

SEPS-4994 GDI-3175: The non-volatile storage shall provide an undetect ...

Y A

SEPS-4995 GDI-3176: The non-volatile reprogrammable storage shall prov ...

Y A

SEPS-4996 GDI-3177: The volatile storage shall provide an undetected b ...

Y A

3.1.4 Venting SEPS-3656 GDI-65:

Provisions shall be implemented in the design of t ... Y R

SEPS-3657 GDI-66: The method of venting shall prevent the release of ...

Y R

SEPS-3658 GDI-59: The equipment/subsystem shall be able to operate w ...

Y A,R

SEPS-3659 GDI-63: Vents shall be < 5mm diameter and > 1.5mm diameter ...

Y R

SEPS-3660 GDI-60: For all relevant thermal hardware, explicitly MLI, ...

Y R

SEPS-3662 GDI-62: Structural members (honeycomb panels, in particula ...

Y R

3.1.5 Interchangeability SEPS-3664 GDI-70:

All spacecraft equipment/subsystems of the same pa ... Y R

3.1.6 Identification & Marking SEPS-3666 GDI-72:

The equipment hardware shall be identified with a ... Y I

SEPS-3667 GDI-73: The equipment/subsystem identification nameplate s ...

Y I

SEPS-3668 GDI-74: For the particular case of connector identificatio ...

Y I

3.1.7 Accessibility/Maintainability & Ground Testing Requirements

SEPS-3670 GDI-82: The design of the equipment/subsystem, the positio ...

Y R

SEPS-3671 GDI-83: The equipment shall be designed to require a minim ...

Y R

SEPS-3672 GDI-84: No field maintenance, servicing or adjustment shal ...

Y R

SEPS-4997 GDI-3155: Items requiring integration, adjustment, servicing ...

Y R


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SEPS-4998 GDI-3156: Items to be removed before flight (red-tag items) ...

Y I

3.1.8 Transportation, Handling and Storage 3.1.8.1 Transport SEPS-3676 GDI-77:

The equipment/subsystems shall be transported usin ... Y R

SEPS-3677 GDI-78: The equipment/subsystem containers, covers (for op ...

Y R

SEPS-3678 GDI-79: The equipment/subsystem transport container shall ...

Y R

SEPS-3679 GDI-80: The equipment/subsystem storage container shall be ...

Y R

SEPS-4999 GDI-3910: The dew point shall never be reached inside the co ...

Y R

SEPS-5000 GDI-3911: The pressure inside the container shall be 10 to 1 ...

Y R


Y R


Y R


Y R

SEPS-5004 GDI-3909: Simple equipment/subsystem container shall be equi ...

Y I


Y R

SEPS-5006 GDI-3913: The IATA flight regulations shall be considered. ...

Y R

SEPS-5007 GDI-3914: For safety reasons, the equipment/subsystem transp ...

Y R

SEPS-5008 GDI-3916: Flight altitude of 30 000 feet shall be considered ...

Y A

SEPS-5009 GDI-3915: Maximum rates of air pressure change: 1,43 mbar/se ...

Y R

3.1.8.2 Equipment/Subsystem Packing SEPS-3681 GDI-90:

Where applicable blanking caps shall be fitted to ... Y I

SEPS-3682 GDI-91: All equipment shall be packaged to ensure that it ...

Y I

SEPS-3683 GDI-93: The specified item GSE shall follow as far as appr ...

Y I

3.1.8.3 Container Identification SEPS-3685 GDI-95:

Each container shall be labelled, tagged or marked ... Y I

SEPS-3686 GDI-96: In addition to the above, the container shall also ...

Y I

SEPS-3687 GDI-2267: Size of company labels on containers shall be agre ...

Y R

3.1.8.4 Handling SEPS-3689 GDI-98:

Equipment/subsystem weighing more than 10 kg shall ... Y R

3.1.9 Seals SEPS-3691 GDI-100:

Any seals used shall comply with all the applicabl ... Y R


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SEPS-3692 GDI-101: Any seals requiring periodic replacement during gr ...

Y R

3.1.10 Lubricants and Sealants SEPS-3694 GDI-103:

No lubricants or sealants shall be used without th ... Y R

3.1.11 Radiation Environment SEPS-5011 GDI-3289:

The spacecraft equipments/subsystems shall be able ... Y A

SEPS-5012 GDI-3292: The equipment/subsystem shall be able to safely wi ...

Y A

SEPS-5013 GDI-3594: SEE in terms of transients are depending on applic ...

Y A

SEPS-5014 GDI-3595: The subcontractor shall perform a displacement ana ...

Y A

SEPS-5015 GDI-3596: With respect to radiation impact, the unit shall b ...

Y A

SEPS-5016 GDI-3336: The procured EEPROM devices shall go through a ade ...

Y R

SEPS-5017 GDI-3337: The circuit design shall implement mechanisms to e ...

Y R

SEPS-5018 GDI-3956: Boot managers shall be implemented in PROM. ...

Y R

SEPS-5019 GDI-3961: The EEPROM case temperature shall be kept lower th ...

Y R

SEPS-5020 GDI-3965: Any subcontractor using EEPROM shall keep trace of ...

Y I

SEPS-5021 GDI-3964: Any onboard software function that writes into EEP ...

Y R

SEPS-5022 GDI-3962: EDAC or use of checksum for each functionally cons ...

Y R

SEPS-5023 GDI-3969: For items known to be sensitive to contamination s ...

Y R

SEPS-5024 GDI-3970: implementation of protective covers which can be e ...

Y R

SEPS-5025 GDI-3971: implementation of purge port allowing the connecti ...

Y R

SEPS-5026 GDI-3972: if necessary, sensitive items shall be kept warmer ...

Y R

SEPS-3696 GDI-105: All drawings, specifications and engineering data ...

Y R

SEPS-3697 GDI-106: Equipment/subsystem shall be compatible with mecha ...

Y R

SEPS-5027 GDI-3818: The unit supplier shall produce a list of the unit ...

Y R

SEPS-5028 GDI-3819: In case that bouncing of relays may lead to interr ...

Y R

SEPS-3701 GDI-2137: Material selection shall be in accordance with ECS ...

Y R

SEPS-3702 GDI-2139: Mechanical parts selection shall be in accordance ...

Y R

SEPS-5029 GDI-3980: All reference frames shall be right-handed orthogo ...

Y R

SEPS-6059 GDI-3982: The MCS coordinate system shall be as defined in F ...

Y R


of 120




3.2.2 Structural Design 3.2.2.1 General Requirements SEPS-3705 GDI-117:

The following failure modes, for equipment/subsyst ... Y A

SEPS-3706 GDI-118: For all structural items the following analyses ar ...

Y A

SEPS-3707 GDI-119: Dynamic Analysis: The dynamic analysis shall show ...

Y A

SEPS-3708 GDI-121: Stress Analysis: For each item a complete stress/s ...

Y A

SEPS-3709 GDI-122: No yielding is allowed at proof load/proof pressur ...

Y T

SEPS-3710 GDI-2053: The structure shall be of adequate strength to wit ...

Y A

SEPS-3711 GDI-2054: Local buckling shall be tolerated only if it is re ...

Y A

SEPS-3712 GDI-2055: For composite materials, microbuckling of fibers s ...

Y A

SEPS-3713 GDI-123: The equipment/subsystem shall be designed to withs ...

Y A

SEPS-3714 GDI-124: For sine and random vibrations, the mechanical siz ...

Y A

SEPS-3715 GDI-125: Wherever practical in the design of the primary st ...

Y A

SEPS-3716 GDI-126: Redundancy concepts (fail-safe) shall be considere ...

Y A

SEPS-3717 GDI-127: Fracture control principles shall be applied where ...

Y A

SEPS-3718 GDI-128: In cases where a fail-safe design cannot be implem ...

Y A

SEPS-3719 GDI-130: A sealed container is a pressurized container, com ...

Y A

SEPS-3720 GDI-131: Pressure lines, fittings and components shall subj ...

Y T

SEPS-3721 GDI-133: All fusion joints shall be 100 %inspected accordin ...

Y I

SEPS-3722 GDI-134: Fasteners used in safe life applications, items fa ...

Y A

SEPS-3723 GDI-135: Fasteners a. Fasteners shall be classified and ana ...

Y A

SEPS-3724 GDI-137: Non-metallic flight structural items (composite, g ...

Y T

SEPS-3725 GDI-138: For load cases involving thermal and/or moisture d ...

Y A

SEPS-3726 GDI-139: Where pressure and/or temperature and/or moisture ...

Y A

SEPS-3727 GDI-140: The Flight equipment shall be able to survive 4 ti ...

Y A

3.2.2.2 Mass Properies SEPS-3729 GDI-143:

All equipment/subsystem suppliers shall provide eq ... Y R


of 120




SEPS-3731 GDI-146: The mass of an item must be measured with the foll ...

Y T

3.2.2.3 Centre of Gravity and Moment of Inertia SEPS-3733 GDI-148:

All COG and MOI estimates shall be accompanied by ... Y A

SEPS-3734 GDI-149: The Center of Gravity (CoG) shall be given. w.r.t. ...

Y R

SEPS-3735 GDI-150: The Moments of Inertia (MoI) shall be given about ...

Y R

3.2.2.4 Stiffness requirements SEPS-3737 GDI-2140:

Minimum natural frequency requirements are imposed ... Y A

SEPS-3738 GDI-154: Except otherwise specified, when equipment/subsyst ...

Y T,A

SEPS-3739 GDI-155: Modal analysis shall be performed to verify the fr ...

Y T,A

SEPS-3742 GDI-2188: The units and associated transport containers shal ...

Y A

SEPS-3743 GDI-2189: Vertical and horizontal loads shall be considered ...

Y A

SEPS-3749 GDI-2199: The transportation containers shall be designed to ...

Y A

SEPS-3750 GDI-2200: The MGSE design and analysis shall consider a desi ...

Y A

SEPS-5030 GDI-3629: During ground transportation the units shall withs ...

Y A

SEPS-5031 GDI-3664: All MGSE, containers, transportation and handling ...

Y A

SEPS-5032 GDI-3665: Sine and random vibrations: the unit transport con ...

Y A

SEPS-5033 GDI-3666: For containers, the shock requirement is a drop of ...

Y T,R

3.2.2.5.2.1 Unit Quasi-Static Loads SEPS-5035 GDI-3670:

The quasi-static and low frequency flight limit ac ... Y A

SEPS-5036 GDI-3671: The loads shall be applied at the unit CoG in out- ...

Y A

3.2.2.5.2.1.1 Units less than or equal to 100kg SEPS-5038 GDI-3673:

The initial unit Design Load (DL) shall be derived ... Y A

SEPS-5039 GDI-3676: After freeze of unit accommodation the design load ...

Y A

SEPS-5040 GDI-3827: During orbit and attitude correction manoeuvres, t ...

Y R

SEPS-5041 GDI-3828: When mounted on spacecraft CFRP panel, the unit s ...

Y A

SEPS-5042 GDI-3997: The insert load carrying capability of GDI-2550 sh ...

Y A

3.2.2.6 Strength requirements 3.2.2.6.1 Definitions and General Requirements SEPS-5043 GDI-3612:

The design load factor philosophy of the unit shal ... Y A

SEPS-5044 GDI-3614: The Flight or Ground Limit Load, LL, is the load t ...

Y A


of 120




SEPS-5045 GDI-3615: Qualification Load, QL is equal to the Limit Load ...

Y A

SEPS-5046 GDI-3616: Design Load, DL is derived by the multiplication o ...

Y A

SEPS-5047 GDI-3617: Yield Load, YL is derived by the multiplication of ...

Y A

SEPS-5048 GDI-3618: Ultimate Load, UL is derived by the multiplication ...

Y A

SEPS-5049 GDI-3619: Yield Factor of Safety, FOSY ensures that unaccept ...

Y A

SEPS-5050 GDI-3620: Ultimate Factor of Safety, FOSU ensures that unacc ...

Y A

SEPS-5051 GDI-3621: Additional Factor of Safety, KADD are additional f ...

Y A

SEPS-5052 GDI-3622: Unit mechanical testing shall take into account an ...

Y A

SEPS-5053 GDI-3623: An additional Protoflight Factor of Safety, FOSPF ...

Y A

3.2.2.6.2 Margins of Safety and Factors of Safety SEPS-3772 GDI-186:

An uncertainty factor Jf shall be defined to provi ... Y A

SEPS-3773 GDI-187: A Qualification Factor of 1.5 shall be used for KQ ...

Y T

SEPS-3774 GDI-188: An Acceptance Factor of 1.0 shall be used for KA t ...

Y A

SEPS-3775 GDI-189: A Design Factor of 1.5 shall be used for DF to det ...

Y A

SEPS-3777 GDI-194: The unit shall be able to withstand, without failu ...

Y A

SEPS-3778 GDI-195: Margin of safety (MOS) a. Margins of safety (MOS) ...

Y A

SEPS-3779 GDI-197: Minimum Factors of Safety against ultimate for pre ...

Y A

SEPS-3780 GDI-198: For combined loads where L(P) is the load due to m ...

Y A

SEPS-3783 GDI-207: Conservative friction coefficients regarding minim ...

Y A

SEPS-3784 GDI-208: Wherever applicable, for general design of bolts, ...

Y R

SEPS-3785 GDI-209: In addition, in case of combined loads due to ther ...

Y A

SEPS-5054 GDI-3398: The design loads for the structure elements are t ...

Y A

SEPS-5055 GDI-3400: The internal loads (thermo elastic, pre-stressed ...

Y A

SEPS-5056 GDI-3401: For sine and random vibrations, the mechanical siz ...

Y A

SEPS-5057 GDI-3402: The margins of safety for all elements of the unit ...

Y A

3.2.3 Design Requirements 3.2.3.1 Mounting Requirements SEPS-3789 GDI-219:

The attachment points of the equipment/subsystem s ... Y R


of 120




SEPS-5058 GDI-3995: The attachment points shall provide a controlled s ...

Y I,R

SEPS-5059 GDI-3996: The mechanical mounting interface shall be consist ...

Y R

SEPS-3790 GDI-220: The number of attachement bolts for a equipment sh ...

Y A

SEPS-3791 GDI-221: The interface plane flatness of a equipment/subsys ...

Y I

SEPS-3792 GDI-222: The equipment/subsystem bolts type and number shal ...

Y R

SEPS-3793 GDI-223: Except otherwise specified, all equipment/subsyste ...

Y R

SEPS-3794 GDI-228: Unless special conditions override, the thickness ...

Y R

SEPS-3795 GDI-229: Minimum clearance between mechanical parts shall c ...

Y R

SEPS-3796 GDI-230: All equipment/subsystems shall be designed allowin ...

Y A

SEPS-3797 GDI-2550: The minimum load carrying capability of the insert ...

Y A,R

SEPS-3798 GDI-2551: The following typical insert distances along the m ...

Y A,R

3.2.3.2 Alignment Requirements SEPS-3800 GDI-232:

Equipment/subsystems requiring alignment with an a ... Y R

SEPS-3801 GDI-233: Optical references are required to withstand all t ...

Y R

SEPS-3802 GDI-234: Location of optical references for equipment/subsy ...

Y R

SEPS-3803 GDI-235: The alignment errors shall be included in pointing ...

Y R

SEPS-3804 GDI-236: Equipment/subsystems which require alignment accur ...

Y R

3.2.4 Mechanical / Optical Interface Control Documents SEPS-3806 GDI-239:

The mechanical and optical configuration and its i ... Y A

SEPS-3807 GDI-240: Interfaces will be subjected to a formal inspectio ...

Y T,I

SEPS-3808 GDI-241: The issues of ICDs have to be released as defined ...

Y A

SEPS-3809 GDI-242: One of the attachment holes on a equipment/subsyst ...

Y R

SEPS-3810 GDI-243: The equipment/subsystem reference frame shall have ...

Y R

SEPS-3811 GDI-244: The equipment/subsystem alignment reference frame ...

Y R

SEPS-3812 GDI-246: The dimensioning of the attachment hole pattern sh ...

Y A

SEPS-3813 GDI-247: Interface Control Drawings shall be provided to AS ...

Y R

3.2.5 Mechanical Mathematical Model Requirements SEPS-3815 GDI-253:

Detailed Finite Element Models (FEM) shall be prov ... Y A


of 120




SEPS-5060 GDI-3830: Detailed Finite Element Models (FEM) shall be prov ...

Y A

SEPS-3816 GDI-254: All FE model requirements, checks and formats are ...

Y T

3.4 Thermal Design and Interface Requirements 3.4.2 Definition of Temperatures and Terms 3.4.2.1 Radiatively Controlled Equipment/Subsystem SEPS-3822 GDI-298:

In the frame of BepiColombo, all equipment/subsyst ... Y R

3.4.2.2 Conductively Controlled Equipment/Subsystem SEPS-3824 GDI-300:

All equipment/subsystems with a power density on t ... Y R

SEPS-5061 GDI-3880: The heater power density shall not exceed 5W per a ...

Y R

3.4.2.3 Isothermal Equipment/Subsystem SEPS-3826 GDI-302:

As far as possible thermal gradients across the ba ... Y R

SEPS-3827 GDI-303: For radiative equipment/subsystems the temperature ...

Y T,A

SEPS-3828 GDI-304: For conductive equipment/subsystems the temperatur ...

Y T,A

SEPS-3829 GDI-305: For non-isothermal equipment/subsystems a referenc ...

Y R

3.4.2.4 Temperature Reference Point (TRP) SEPS-3831 GDI-307:

The temperature reference point (TRP) shall be sel ... Y R

SEPS-5062 GDI-3876: The system interface temperature point (STP) if de ...

Y T,A

SEPS-5063 GDI-3882: The equipment/unit supplier shall analyse the heat ...

Y A

3.4.3 Thermal Interface Requirements 3.4.3.1 Conductive Interface SEPS-3834 GDI-316:

The mounting interface shall comply with the mecha ... Y A

SEPS-3835 GDI-317: Equipment/subsystem mounting areas shall not be pa ...

Y R

SEPS-3836 GDI-318: All equipment/subsystems shall have a smooth and p ...

Y R

SEPS-3837 GDI-319: Local heat flux shall not be greater than 1.5x spe ...

Y A

SEPS-3838 GDI-2536: An interface filler with a coefficient of friction ...

Y R

3.4.3.2 Radiative Interface SEPS-3840 GDI-322:

Equipment/subsystems shall be designed with an emi ... Y R

3.4.3.3 Internal Temperature Monitoring SEPS-3842 GDI-324:

Temperature monitoring of selected points within a ... Y R

SEPS-3843 GDI-325: The location, type and electrical interface of all ...

Y R

3.4.4 Thermal Design Requirements SEPS-5064 GDI-3184:

Dimensioning of the Thermal Control of space expos ... Y A


of 120




SEPS-5065 GDI-3881: Dimensioning of the standard Equipment/UnitThermal ...

Y A

SEPS-3845 GDI-327: The equipment/subsystems shall be designed such th ...

Y A

SEPS-5066 GDI-3185: All space exposed items shall be able to withstand ...

Y T,A

SEPS-5067 GDI-3188: Use of materials with non-stable thermo-optical pr ...

Y T,R

SEPS-5068 GDI-3193: It shall be possible to demonstrate conformance of ...

Y T,A

SEPS-5069 GDI-3203: Calculated temperatures of external materials shal ...

Y A

SEPS-5070 GDI-3967: Every equipment/unit/subsystem which is exposed to ...

Y A

3.4.5 Thermal Control SEPS-3847 GDI-331:

All thermal hardware mounted on the equipment/subs ... Y R

3.4.6 Thermal Interface Control Documents SEPS-3849 GDI-333:

All equipment/subsystem thermal interfaces shall b ... Y R

3.4.7 Thermal Mathematical Model Requirements SEPS-5071 GDI-3201:

The compliance to the thermal performance requirem ... Y A

SEPS-5072 GDI-3202: In case of TB test execution, the temperature unce ...

Y A

3.4.7.2 Thermal Interface Modeling SEPS-3852 GDI-336:

The Thermal mathematical model shall be provided f ... Y A

SEPS-3853 GDI-337: SI units: All units used in thermal models (geomet ...

Y A

3.4.7.3 Thermal Model Correlation SEPS-3855 GDI-339:

The detailed thermal model of a equipment/subsyste ... Y T,A

3.4.7.4 Reduced Thermal Model SEPS-3857 GDI-341:

The consistency between reduced and detailed therm ... Y A

SEPS-3858 GDI-342: The convergence of the thermal models shall be dem ...

Y A

3.6 Electrical Design and Interface Requirements 3.6.1 General Requirements SEPS-3861 GDI-380:

All electrical performances are specified under Wo ... Y R

SEPS-3862 GDI-381: Beginning-Of-Life criteria shall be derived by the ...

Y R

3.6.2 Electrical Power 3.6.2.1 Power Requirements and Budgets SEPS-3866 GDI-1824:

For all units with a primary power consumption whi ... Y R

SEPS-3867 GDI-1825: The power for telemetry conditioning of equipment ...

Y R

3.6.2.2 Failure Containment and Redundancy SEPS-3869 GDI-1826:

Any protection feature supporting essential functi ... Y R


of 120




SEPS-3870 GDI-1827: With the exception of protection features such as ...

Y A

SEPS-3871 GDI-1828: Recovery of primary power shall be possible in any ...

Y A

3.6.2.3 Power Conditioning and Control SEPS-3873 GDI-1830:

The phase margin of converters and regulators shal ... Y T,A

SEPS-3874 GDI-1832: The electrical zero-volt reference of isolated con ...

Y T

SEPS-3875 GDI-1833: The capacitance between the zero-volt reference of ...

Y T

SEPS-3876 GDI-1834: If a switching converter is externally synchronise ...

Y R

SEPS-3877 GDI-1835: Under the occurrence of any single failure, the co ...

Y A

SEPS-6060 GDI-3991: The requirements on electrical power user interact ...

Y R

SEPS-6061 GDI-3992: All load requirements shall be verified by test. ...

Y T

SEPS-6062 GDI-3205: No load shall generate a spurious response that ca ...

Y T

3.6.2.4 Power Distribution and Protection SEPS-6063 GDI-3296:

All otherwise non-protected sections of a main bus ... Y T,A

SEPS-3879 GDI-393: Fuses shall not be used. ...

Y R

SEPS-5073 GDI-3206: Relays shall be protected such that the peak volta ...

Y T,A

SEPS-5074 GDI-3207: Equipment connected to independent, redundant powe ...

Y A

SEPS-5075 GDI-3208: All current limiting devices and automatic switch ...

Y T,A

SEPS-5076 GDI-3209: All protection elements shall be designed such tha ...

Y T

SEPS-5077 GDI-3210: All Latching Current Limiters (LCL) shall provide ...

Y T

3.6.2.4.1 28V Regulated Power Requirements SEPS-3881 GDI-410:

All equipment/subsystems connected to the regulate ... Y T,A

SEPS-3882 GDI-411: If undervoltage protection is implemented by the l ...

Y T

SEPS-3883 GDI-412: In case of an inductive load, the load shall preve ...

Y T,A

SEPS-3884 GDI-413: The load shall not be irreversibly degraded for an ...

Y R

SEPS-3885 GDI-415: No primary current protection shall be implemented ...

Y R

SEPS-3886 GDI-417: All electronic logic equipment/subsystems/circuits ...

Y I,R

SEPS-3887 GDI-418: All power converters shall work in free-running mo ...

Y T

SEPS-3888 GDI-419: The free-running frequency shall be limited to ±10 ...

Y T


of 120




SEPS-3889 GDI-420: The as designed free-running frequency and frequen ...

Y T

SEPS-3890 GDI-421: The equipment/subsystems shall be designed taking ...

Y A

SEPS-3891 GDI-416: 28V Regulated Latching Current Limiter Interface C ...

Y T

SEPS-3892 GDI-424: 28V Regulated Fold-Back Current Limiter Interface ...

Y T

SEPS-3893 GDI-426: Following switch-ON, and during input filter charg ...

Y T,R

3.6.2.4.2 100V Regulated Power Interface Requirements (TBC)

SEPS-3895 GDI-389: All equipment/subsystems connected to the 100V Reg ...

Y T,A

SEPS-5078 GDI-3917: All equipment/subsystems connected to the 100V Reg ...

Y T,A

SEPS-3896 GDI-3128: During battery charge and discharge the 100V Regul ...

Y T,A

SEPS-3898 GDI-391: In case of an inductive load, the load shall preve ...

Y T,A


Y A


Y A

SEPS-5080 GDI-3373: For 100V Regulated Power Bus users, the following ...

Y A

SEPS-3901 GDI-396: All electronic logic equipment/subsystems/circuits ...

Y I,R

SEPS-3902 GDI-397: All power converters shall work in free-running mo ...

Y T

SEPS-3903 GDI-398: The free-running frequency shall be limited to ± 1 ...

Y T

SEPS-3904 GDI-399: The as designed free-running frequency and frequen ...

Y T

SEPS-3905 GDI-400: Equipments/subsystems connected to the High Curren ...

Y A

SEPS-5081 GDI-3372: Primary current protection shall be implemented on ...

Y T,R

SEPS-5082 GDI-3920: Equipments/subsystems connected to the Low Current ...

Y A

SEPS-3900 GDI-394: No primary current protection shall be implemented ...

Y R

SEPS-3897 GDI-390: If undervoltage protection is implemented by the l ...

Y T

SEPS-3906 GDI-395: Low Current 100V LCL Power Interface Characteristi ...

Y T

3.6.2.4.3 Power Consumption Requirements SEPS-3908 GDI-433:

The compliance versus the power allocations shall ... Y T,A

SEPS-3909 GDI-434: For each power interface circuit, the following co ...

Y T,A

SEPS-3910 GDI-435: A power consumption test shall be required at temp ...

Y T,R

3.6.2.4.4 Tolerance to Power Bus Failures


of 120




SEPS-3912 GDI-437: When a equipment/subsystem is internally redundant ...

Y T,A

3.6.2.4.5 Initial Electrical Status SEPS-3914 GDI-439:

After being switched ON, equipment shall have a sa ... Y T

3.6.2.4.6 Special Case: Secondary Power Supplied by equipment/subsystems

SEPS-3916 GDI-442: It shall be possible to switch on the source equip ...

Y T

SEPS-3917 GDI-443: The source equipment/subsystem shall be protected ...

Y T

SEPS-3918 GDI-444: The supplied equipment/subsystem and Electrical I/ ...

Y T,A

3.6.2.5 High Voltage Engineering SEPS-3920 GDI-1850:

High voltage equipments shall be designed and manu ... Y A

SEPS-3921 GDI-1851: The design of high voltage equipment shall be such ...

Y A

SEPS-3922 GDI-1852: The field enhancement factors shall be controlled ...

Y A

SEPS-3923 GDI-1853: For high voltage equipment design and testing, vac ...

Y A

SEPS-3924 GDI-1854: For potted circuits, the glass transition point of ...

Y A

SEPS-3925 GDI-1855: The minimum bend radius for high voltage cables sh ...

Y A

3.6.4 MIL-STD-1553B Bus Interface 3.6.4.1 Definitions 3.6.4.2 General Requirements SEPS-3930 GDI-3090:

Each BepiColombo MIL-STD-1553B Bus system shall be ... Y R

SEPS-3931 GDI-3091: Each data bus system shall function asynchronously ...

Y R

SEPS-3932 GDI-465: Each equipment/subsystem (flight, Ground/EGSE) con ...

Y T,R

SEPS-3933 GDI-466: All equipment/subsystems connected to the bus shal ...

Y R

SEPS-3934 GDI-467: Internally redundant equipment shall be connected ...

Y R

SEPS-3935 GDI-3092: A single event failure to a data bus (A or B) shal ...

Y A

SEPS-3936 GDI-2734: Digital data shall be transmitted in a form compat ...

Y R

SEPS-3937 GDI-2735: The bit priority shall be as defined in [SD-1] par ...

Y R

3.6.4.3 Transmission Method SEPS-3939 GDI-2756:

The signal modulation shall comply to [SD-1] para ... Y T

SEPS-3940 GDI-2729: The data coding (Manchester II bi-phase) shall com ...

Y T

SEPS-3941 GDI-2730: The transmisssion bit-rateshall comply to [SD-1] p ...

Y T

SEPS-3942 GDI-2731: The word size shall comply to [SD-1] para 4.3.3.5. ...

Y T


of 120




SEPS-3943 GDI-2732: The word formats (command , data, status words) sh ...

Y T

SEPS-3944 GDI-3094: The Message/Transfer formats shall comply to [SD-1 ...

Y T

SEPS-3945 GDI-3096: The BC shall provide a minimum gap time between me ...

Y T

SEPS-3946 GDI-3106: The RT shall provide a Response Time according to ...

Y T

SEPS-3947 GDI-3097: Minimum No-Response Time-out shall comply to [SD-1 ...

Y T

3.6.4.4 BC/RT Operation SEPS-3949 GDI-3113:

A BC shall operate according to [SD-1] para 4.4.1 ...

Y T

SEPS-3950 GDI-3114: A RT shall operate according to [SD-1] para 4.4.1 ...

Y T

SEPS-3951 GDI-2753: For a dual-redundant RT, a separate fail-safe time ...

Y A

3.6.4.5 Data Bus Requirements SEPS-3953 GDI-2721:

Each BepiColombo MIL-STD-1553B data bus shall comp ... Y R

SEPS-3954 GDI-2722: The Bus-Cable (core bus and stubs) shall comply to ...

Y R

SEPS-3955 GDI-2723: The Cable-Terminations (at each main bus end) shal ...

Y R

SEPS-3956 GDI-2724: Bus-Couplers (transformer coupled stub type) shal ...

Y R

SEPS-3957 GDI-2725: Spacecraft skin connector(s) providing Stub connec ...

Y R

SEPS-3958 GDI-2726: Spacecraft skin connector(s) at the end of each co ...

Y R

SEPS-3959 GDI-2733: The maximum length of a long stub (distance from t ...

Y R

SEPS-3960 GDI-2727: Each BepiColombo MIL-STD-1553B bus (MPO, MTM, MMO) ...

Y T,A

SEPS-3961 GDI-2736: The core bus test extension shall implement: the ...

Y A

SEPS-3962 GDI-2737: The core bus test extension shall implement: the ...

Y A

3.6.4.5.1 Data Bus Connector SEPS-3964 GDI-470:

The BepiColombo MIL-STD-1553B data busses (MPO, MT ... Y R

SEPS-3965 GDI-471: Unless otherwise agreed with ASD, the MIL-STD-1553 ...

Y R

SEPS-3966 GDI-2739: In case single failure requirements cannot be achi ...

Y A,R

3.6.4.6 BC/RT Signal Characteristics SEPS-3968 GDI-2719:

The electrical output characteristics (transformer ... Y T


of 120




SEPS-3969 GDI-2728: The electrical input characteristics (transformer ...

Y T

3.6.4.7 Remote Terminal (RT) Physical Address SEPS-3971 GDI-2741:

The RT terminal address shall be wire-programmable ... Y R

SEPS-3972 GDI-2742: Each RT as identified in Figure GDI-473 shall prov ...

Y R

SEPS-3973 GDI-2743: Unless otherwise agreed with ASD, no other signals ...

Y R

SEPS-3974 GDI-2268: Unless otherwise agreed with ASD, each RT shall pr ...

Y R

SEPS-3975 GDI-2744: The RT terminal address shall be set on the mating ...

Y R

SEPS-3976 GDI-2747: When connected to the unit electrical ground, logi ...

Y R

SEPS-3977 GDI-2750: The RT address plug shall be furnished with the un ...

Y I

3.6.4.8 Protocol Requirements 3.6.4.9 RemoteTerminal Test Requirements SEPS-3981 GDI-2425:

Each 1553 function is considered being split in 3 ... Y R

SEPS-3982 GDI-2426: The tests corresponding to [SD-2] Section 100 “RT ...

Y T

SEPS-3983 GDI-2427: The general test requirements of [SD-2] Section 10 ...

Y T

SEPS-3984 GDI-2244: The general monitoring requirements of [SD-2] Sect ...

Y T

SEPS-3985 GDI-2552: RT tests (Electrical and Protocol Tests) shall be ...

Y T

SEPS-3986 GDI-2553: The test paragraphs defined in [SD-2] section 100 ...

Y T

3.6.4.9.1 RT Electrical Tests SEPS-3988 GDI-2428:

Output characteristic test corresponding to [SD-2] ... Y T

SEPS-3989 GDI-2429: Output characteristic test corresponding to [SD-2] ...

Y T


Y T


Y T


Y T


Y T


Y T


Y T


Y T


Y T


Y T


of 120




SEPS-3999 GDI-2439: Input characteristic test corresponding to [SD-2] ...

Y T


Y T


Y T


Y T


Y T


Y T

3.6.4.9.2 RT Protocol Tests SEPS-4006 GDI-2448:

Protocol tests corresponding to [SD-2] Section 100 ... Y T

SEPS-4007 GDI-2449: Protocol tests (Intermessage gap) corresponding to ...

Y T

SEPS-4008 GDI-2450: Protocol tests (Error Injection) corresponding to ...

Y T


Y T


Y T


Y T


Y T


Y T


Y T

SEPS-4015 GDI-2457: Protocol tests corresponding to [SD-2] Section 100 ...

Y T


Y T


Y T


Y T


Y T

SEPS-4020 GDI-2558: Protocol tests (Optional mode commands) correspond ...

Y T


Y T


Y T


Y T


Y T


Y T


of 120





Y T


Y T

SEPS-4028 GDI-2561: Protocol tests (Status word bits) corresponding to ...

Y T


Y T

SEPS-4030 GDI-2563: Protocol tests (Broadcast mode commands) correspon ...

Y T


Y T


Y T


Y T

SEPS-4034 GDI-2567: Protocol tests (Error´injection - broadcast messag ...

Y T

3.6.4.9.3 RT Noise Rejection Test SEPS-4036 GDI-2446:

A Test corresponding to [SD-2] Section 100, para 5 ... Y T

SEPS-5083 GDI-3142: The general test and requirements of the Validatio ...

Y T

SEPS-5084 GDI-3143: The general monitoring requirements of the Validat ...

Y T

SEPS-5085 GDI-3148: Protocol tests corresponding to SAE AS4113, para 5 ...

Y T

SEPS-5086 GDI-3149: Protocol tests corresponding to SAE AS4113, para 5 ...

Y T

SEPS-5087 GDI-3151: A Test corresponding to SAE AS4113, para 5.3 "Nois ...

Y T

3.6.6 Discrete Standard Signal Interfaces 3.6.6.1 General Definitions and Conventions SEPS-4039 GDI-450:

Specified driver (or source) characteristics shall ... Y R

SEPS-4040 GDI-451: All data and signal interface drivers shall surviv ...

Y T,A

SEPS-4041 GDI-452: The equipment/subsystem shall tolerate active sign ...

Y T,A

SEPS-4042 GDI-453: In case the electrical architecture does foresee c ...

Y T,R

SEPS-4043 GDI-454: In case no load is specified, the interface charac ...

Y R

3.6.6.2 Interface Control during Power Cycling SEPS-4045 GDI-2278:

Input interfaces shall not be damaged or harmed du ... Y A

SEPS-4046 GDI-2279: Output interfaces shall not be damaged or harmed d ...

Y A

SEPS-4047 GDI-2280: For pulse commands it shall be ensured that spurio ...

Y A

3.6.6.3 Standard Serial Digital Interfaces SEPS-4049 GDI-478:

The SBDL interface is dedicated to serial digital ... Y R


of 120




SEPS-4050 GDI-486: Standard Balanced Digital Link interface: The (sub ...

Y T

SEPS-4051 GDI-2496: The following conditions shall apply for use of th ...

Y R

SEPS-4052 GDI-2497: The SBDL receiver implementation shall allow to po ...

Y R

3.6.6.3.2 Low Voltage Differential Signals (LVDS) SEPS-4054 GDI-2283:

The LVDS interface is dedicated to serial digital ... Y R

SEPS-4055 GDI-2285: Low Voltage Digital Signal interface: The (sub-)co ...

Y T

3.6.6.4.1 Analogue Telemetry Acquisition (AN1) SEPS-4057 GDI-511:

Analogue telemetry Acquisition -5V to +5V interfac ... Y T

3.6.6.4.2 Analogue Telemetry Acquisition (AN2) SEPS-4059 GDI-513:

Analogue telemetry Acquisition 0 to +5V interface: ... Y T

3.6.6.5 Temperature Acquisitions 3.6.6.5.1 Thermistor Type 1: YSI-44907/YSI-44908 (ANY) SEPS-4062 GDI-523:

Temperature Acquisition Type 1: YSI-44907/YSI-4490 ... Y T

3.6.6.5.2 Thermistor Type 2: PT-1000 (ANP) SEPS-4064 GDI-526:

Temperature Acquisition Type 2: PT-1000 (ANP) inte ... Y T

3.6.6.6 Bi-level Signal Acquisition 3.6.6.6.1 Bi-level Digital Interface SEPS-4069 GDI-549:

Each bi-level digital channel shall be used to acq ... Y R

SEPS-4070 GDI-550: Bi-Level Digital TM Acquisition Interface The (sub ...

Y T

3.6.6.6.2 Relay / Switch Status Interface SEPS-4072 GDI-488:

The open/closed status of a relay/switch contact o ... Y T

SEPS-4073 GDI-489: The Relay / Switch Status interface receivers shal ...

Y A,R

SEPS-4074 GDI-546: Relay / Switch Status Acquisition Interface The (s ...

Y T

3.6.6.7 High Power Command Interfaces SEPS-4076 GDI-530:

The High Power On/Off Command source shall be refe ... Y R

SEPS-4077 GDI-531: The High Power On/Off Command receiver shall be is ...

Y R

SEPS-4078 GDI-532: The High Power On/Off Command receiver shall be eq ...

Y R

SEPS-4079 GDI-533: The High Power On/Off Command source circuit shall ...

Y R

SEPS-4080 GDI-539: The (sub-)contractor High Power On/Off Command sou ...

Y R

SEPS-4081 GDI-540: The control of the pulse width shall be managed au ...

Y T


of 120




3.6.6.7.1 Standard High Power Command SEPS-4083 GDI-534:

Standard High Power On/Off Command: The (sub-)cont ...

Y T

3.6.6.7.2 Extended High Power Command SEPS-4085 GDI-536:

Extended High Power Command: The (sub-)contractor ...

Y T

3.6.6.8 Synchronisation Signals SEPS-4087 GDI-496:

The active level shall be High level ... Y R

SEPS-4088 GDI-500: The synchronisation reference shall be the leading ...

Y R

3.6.6.8.1 Pulse Per Second Interface SEPS-4090 GDI-494:

The Pulse Per Second interface (IF-Code PPS) shall ... Y T

SEPS-4091 GDI-495: Pulse periode T shall be 1 sec (Pulse frequency s ...

Y T,A

SEPS-4092 GDI-497: The accuracy of the PPS signal shall be 10-7 over ...

Y T

SEPS-4093 GDI-498: The pulse width Tw of the PPS signal shall be 1 ms ...

Y T

SEPS-4094 GDI-502: The jitter of the PPS signal shall be < 10 ns (tbc ...

Y T

3.6.6.8.2 AOCS Synchronisation Pulse Interface SEPS-4096 GDI-499:

The AOCS Synchronisation Pulse interface (IF-Code ... Y R

SEPS-4097 GDI-504: The (sub-)contractor shall design his side of the ...

Y T

SEPS-4098 GDI-2246: The Repetition rate of the ASP signal shall be 8 H ...

Y T

SEPS-4099 GDI-2248: The pulse width Tw of the ASP signal shall be 15 m ...

Y T

SEPS-4100 GDI-2249: The jitter of the ASP signal shall be < 1.0 ms (tb ...

Y T

3.6.6.9 Communication System Interfaces 3.6.6.9.1 Digital TC Channel Interface SEPS-4103 GDI-554:

The Digital TC Channel shall consist of the follow ... Y R

SEPS-4104 GDI-555: The Data, Clock and Data-Valid signals shall be tr ...

Y R

SEPS-4105 GDI-556: For Data, Clock and Data-Valid signals, the (sub-) ...

Y T

SEPS-4106 GDI-2505: For TC Data-Valid signal, the SBDL receiver shall ...

Y T,A

SEPS-4107 GDI-2507: The data stream shall be (PCM) NRZ-L (data from th ...

Y T


Y T


Y T

SEPS-4110 GDI-2503: The Receiver Lock Status (RLS) signal shall be tra ...

Y R


of 120




SEPS-4111 GDI-2504: For the Receiver Lock Status (RLS) signal, the (su ...

Y T

SEPS-4112 GDI-2506: For the Receiver Lock Status (RLS) signal a high v ...

Y R

3.6.6.9.2 Digital TM Channel Interface SEPS-4114 GDI-565:

The Digital TM Channel shall consist of the follow ... Y R

SEPS-4115 GDI-566: The Data, Clock and Data-Valid signals shall be tr ...

Y R


Y T

SEPS-4117 GDI-2509: The TM data stream shall be (PCM) NRZ-L with the f ...

Y T


Y T

SEPS-4119 GDI-2511: Option: In addition the (sub-)contractor shall pro ...

Y T


Y T

3.6.7 Cross Strapping SEPS-4123 GDI-614:

For 2 equipment/subsystems (equipment/subsystem_1 ... Y R

SEPS-4124 GDI-616: Number of links: The equipment/subsystem_2_A I/F s ...

Y R

SEPS-4125 GDI-617: IMMUNITY at equipment/subsystem_2 level (Receiver ...

Y R

SEPS-4126 GDI-618: PROTECTIONS at equipment/subsystem_1 Driver level ...

Y R

SEPS-4127 GDI-619: PROTECTIONS at equipment/subsystem_2 receiver leve ...

Y R

3.6.8 Connectors and Harness General Design Requirements

SEPS-4129 GDI-574: The spacecraft harness categorisation into EMC cla ...

Y R

SEPS-4130 GDI-2576: Equipment/subsystems shall use a separate connecto ...

Y R

SEPS-4131 GDI-2577: Signals falling into different EMC categories shal ...

Y R

SEPS-4132 GDI-583: Nominal and redundant lines/functions shall be rou ...

Y R

SEPS-4161 GDI-592: All unterminated equipment or harness connectors s ...

Y I,R

SEPS-4162 GDI-593: All arming plugs shall be protected by EMC backshe ...

Y R

3.6.8.1 Connector Types SEPS-4134 GDI-572:

All connectors mounted on equipment/subsystems and ... Y R

SEPS-4135 GDI-2575: Where non-standard connector, inserts, or round co ...

Y R

SEPS-4136 GDI-582: Connectors shall be made of Non-magnetic material ...

Y R

SEPS-4137 GDI-573: The number times flight connectors are mated / dem ...

Y R


of 120




3.6.8.2 Connector Characteristics SEPS-4139 GDI-576:

Connectors at interfaces shall be clearly identifi ... Y R

SEPS-4140 GDI-577: Equipment or structure-mounted connectors/contacts ...

Y R

SEPS-4141 GDI-578: As far as possible, the connector type used for pr ...

Y R

SEPS-4142 GDI-2588: The EED mating (harness) connector shall be of MS ...

Y R

SEPS-4143 GDI-2585: If power and other signal connectors are located a ...

Y R

SEPS-4144 GDI-587: Mechanical methods in conjunction with identificat ...

Y R

SEPS-4145 GDI-610: All connectors shall be marked unambiguously. Labe ...

Y R

SEPS-4146 GDI-2578: Equipment or structure-mounted connectors shall be ...

Y R

SEPS-4147 GDI-581: Each signal and its corresponding return shall, wh ...

Y R

SEPS-4148 GDI-2579: An adequate number of spare contacts shall be made ...

Y R

SEPS-4149 GDI-2580: If a connector contains only shielded wires only 8 ...

Y R

SEPS-4150 GDI-2581: Connectors shall be fully equipped with contacts ( ...

Y I

SEPS-4151 GDI-589: At least one contact per equipment connector shall ...

Y R

SEPS-4152 GDI-2583: In case several shield connections through a conne ...

Y R

3.6.8.3 Connector Mounting SEPS-4154 GDI-585:

All electrical connectors shall be located at a mi ... Y R

SEPS-4155 GDI-586: Connectors shall be arranged in such a way that th ...

Y R

SEPS-4156 GDI-2582: D*M(A)-type connectors mounting clearances shall b ...

Y I,R

SEPS-4157 GDI-580: Male and female connectors shall be mechanically l ...

Y I

SEPS-5088 GDI-3950: For D*M(A)-type connectors the wall thickness shal ...

Y R

SEPS-5089 GDI-3951: For D*M(A)-type connectors the female screw lock a ...

Y R

SEPS-4158 GDI-588: Connector savers shall be utilized on all flight s ...

Y I

3.6.8.4 Test Connectors SEPS-4160 GDI-591:

Test connectors shall have sufficient protection t ... Y R

3.6.8.5 Cabling / Wiring SEPS-5090 GDI-3124:

No piece of harness shall be used as a mechanical ... Y R

SEPS-5091 GDI-3125: For transmission of power, each line shall be twis ...

Y R

SEPS-5092 GDI-3211: The power distribution shall be protected in such ...

Y A


of 120




SEPS-5093 GDI-3127: The harness inductance for a fully regulated bus, ...

Y A

SEPS-4165 GDI-2587: For the power harness redundant contacts and wirin ...

Y R

SEPS-4166 GDI-595: Cables falling into different EMC categorisations ...

Y R

SEPS-4167 GDI-596: All cable bundles shall be routed as close as poss ...

Y I,R

SEPS-4169 GDI-598: The DC resistance between the single cable shield ...

Y T

SEPS-5094 GDI-2589: Electrical supply for each EED shall be by a separ ...

Y R

SEPS-4170 GDI-2590: Connections to the pyro initiators shall be capabl ...

Y R

SEPS-4171 GDI-2591: The safe plug shall short-circuit and ground each ...

Y R

SEPS-4172 GDI-2592: The arming plug shall provide electrical continuit ...

Y R

3.6.8.6 Cable and Harness Shields SEPS-4179 GDI-611:

To achieve a complete Faraday-cage around the harn ... Y R

SEPS-4174 GDI-600: Where shielded wires are used, the shield shall be ...

Y R

SEPS-4175 GDI-601: The structure termination of shields shall be made ...

Y I,R

SEPS-4176 GDI-602: The maximum unshielded length of any shielded wire ...

Y R

SEPS-4177 GDI-603: Daisy chaining of shield terminations shall be avo ...

Y R

SEPS-4178 GDI-604: Shields shall not be used as an intentional curren ...

Y R

SEPS-4180 GDI-612: Overall shields shall be terminated to the connect ...

Y R

3.6.8.7 Harness Capacitance SEPS-4182 GDI-607:

Interface signal drivers shall consider the capaci ... Y A

3.6.9 Electrical Interface Control Document SEPS-4184 GDI-621:

Interfaces will be formally controlled within the ... Y R

SEPS-4185 GDI-2574: Electrical interface control data shall be transfe ...

Y R

3.7 Operations Design and Interface Requirements 3.7.1 Bit / Byte Numbering Convention SEPS-4188 GDI-624:

In all project specific documentation including co ... Y T,R

SEPS-4189 GDI-626: For serial data transfer, within any data type str ...

Y T,R

SEPS-4190 GDI-2535: For MIL-STD-1555B bus systems, the bit/byte number ...

Y T,R

SEPS-5095 GDI-3892: For ECSS-E-50-12A SpaceWire interfaces, the bit/by ...

Y T,R

SEPS-4531 GDI-746: The following standardization (Table GDI-747) shal ...

Y R

3.8 Software


of 120




3.8.1 General SEPS-5096 GDI-3403:

The system engineering process related to software ... Y R

SEPS-4540 GDI-763: Data Type Representation and Data Value Representa ...

Y R

3.8.2 Software Design and Interfaces SEPS-4544 GDI-2548:

The equipment/subsystem shall implement the functi ... Y T

SEPS-4545 GDI-2549: It shall be possible to trigger the reset and/or c ...

Y T

SEPS-4547 GDI-1105: All onboard software shall be developed using a hi ...

Y R

SEPS-4548 GDI-759: No high level programming language, real time kern ...

Y R

SEPS-4535 GDI-752: Software execution shall be deterministic and oper ...

Y T,R

SEPS-4577 GDI-1116: Software shall be segmented into modules by functi ...

Y R

SEPS-4578 GDI-1117: Each module shall be further segmented into code, ...

Y R

SEPS-4579 GDI-1120: All input and output data for each module shall be ...

Y R

SEPS-4580 GDI-1121: It shall be possible to compile a module as a stan ...

Y T,TBC

SEPS-4581 GDI-1122: A module shall not clear or otherwise modify input ...

Y R

SEPS-4582 GDI-1123: Each data element that is passed between modules s ...

Y T

SEPS-4606 GDI-1141: The software shall feature a modular structure, i. ...

Y R

SEPS-4583 GDI-1124: The software shall be built using references to th ...

Y T,R

SEPS-4584 GDI-1125: If required the service 22 shall be used to save t ...

Y T

SEPS-4585 GDI-1126: The resources utilised by onboard software shall b ...

Y T

SEPS-4549 GDI-1106: The software developed shall be in two stand-alone ...

Y T,R

SEPS-4550 GDI-815: The Initialisation S/W shall support a minimum sub ...

Y T

SEPS-4551 GDI-777: The Software package (Initialisation and Applicati ...

Y T,A

SEPS-4552 GDI-779: Release/Version information shall be hard-coded wi ...

Y R

SEPS-4553 GDI-780: Release/Version information shall be reported on r ...

Y T

SEPS-4554 GDI-781: The equipment/subsystem shall contain a non-volati ...

Y R

SEPS-4555 GDI-782: The non-volatile memory of the Initialisation S/W ...

Y R

SEPS-4565 GDI-808: The Initialisation S/W shall support the communica ...

Y T

SEPS-4557 GDI-798: The Initialisation S/W shall generate a boot repor ...

Y T


of 120




SEPS-4559 GDI-805: The Initialisation S/W shall have the capability t ...

Y T


Y T


Y T

SEPS-4560 GDI-799: The Initialisation S/W shall complete the so-calle ...

Y T

SEPS-4568 GDI-795: The Initialisation S/W shall NEVER reach HALT (e.g ...

Y T

SEPS-4558 GDI-2547: A failed test shall not lead to a dead lock of the ...

Y T

SEPS-4575 GDI-800: The Application S/W shall be started upon TC reque ...

Y T

SEPS-4570 GDI-796: If the application software will enter unforeseen ...

Y T

SEPS-4335 GDI-729: It shall be possible to store the uploaded equipme ...

Y T

SEPS-4605 GDI-1140: Where possible FDIR shall be implemented in separa ...

Y R

SEPS-4587 GDI-1128: Whenever a condition that forces a processor reset ...

Y T

SEPS-4538 GDI-761: The error context information shall include as a m ...

Y T

SEPS-4607 GDI-1143: Software shall not need to react at high speed to ...

Y A

SEPS-4588 GDI-1129: Whenever a processor is running synchronously sche ...

Y T

SEPS-4595 GDI-1130: Whenever a processor overload condition is detecte ...

Y T

SEPS-4589 GDI-754: Scheduler overruns shall be detected and reported ...

Y T

SEPS-4590 GDI-755: Schedule overruns shall not lead into uncompleted ...

Y R

SEPS-4591 GDI-2546: After a predefined number of consecutive or recurr ...

Y T

SEPS-4596 GDI-1131: Whenever an unexpected arithmetic overflow conditi ...

Y T

SEPS-4597 GDI-1132: Whenever an illegal programme instruction is encou ...

Y T

SEPS-4598 GDI-1133: Whenever a data bus error is detected by software, ...

Y T

SEPS-4599 GDI-1134: Whenever a memory corruption is detected by an err ...

Y A,TBC

SEPS-4600 GDI-1135: Whenever a checksum error is detected, an event re ...

Y T

SEPS-4601 GDI-1136: A processor should perform internal consistency ch ...

Y R,TBC

SEPS-4602 GDI-1137: Whenever an internal inconsistency is detected, an ...

Y T

SEPS-4603 GDI-1138: The event reports that are generated in the case o ...

Y T

SEPS-4604 GDI-1139: The system shall ensure that safety critical softw ...

Y A,R


of 120




SEPS-4608 GDI-1144: The onboard software shall perform a continuous me ...

Y A,R

SEPS-4609 GDI-1145: When a single bit error is detected, the memory ad ...

Y A,TBC

3.8.3 Software Performance SEPS-4611 GDI-1112:

The images of initialisation software shall be con ... Y A,R

SEPS-4612 GDI-1113: The image for the mission software shall be contai ...

Y A,R

SEPS-4613 GDI-1114: The executable image of the mission software shall ...

Y A,R

SEPS-4614 GDI-1115: The mission software shall not use more than 75% o ...

Y A,TBC

SEPS-4615 GDI-1118: Each module shall be allocated 5% spare memory are ...

Y A,TBC

SEPS-4616 GDI-1119: When a processor cannot support the direct address ...

Y A,TBC

3.8.4 Maintenance during Flight SEPS-4618 GDI-1149:

The full development, test and maintenance environ ... Y R

SEPS-4628 GDI-1159: The software test environment used pre-launch has ...

Y R

SEPS-4619 GDI-1150: The complete software development environment shal ...

Y R

SEPS-4620 GDI-1151: The development environment shall include (list no ...

Y R

SEPS-4622 GDI-1153: The full software development and maintenance envi ...

Y T

SEPS-4626 GDI-1157: The capability shall be provided to check that onb ...

Y T

SEPS-4627 GDI-1158: Enabling of onboard software shall use only a sing ...

Y T

3.8.5 Software Test Bed / Software Validation Facility SEPS-4630 GDI-1163:

A Software Test Bed (STB) shall be used by each so ... Y R

3.8.6 Independent Software Verification and Validation 5.1 Mechanical Interface Datasheet SEPS-4685 GDI-2760:

The mechanical and optical configuration and its i ... Y R

6.1 Thermal Interface Control Document SEPS-4687 GDI-2892:

All unit thermal interfaces shall be described wit ... Y R

7.1 Electrical Interface Datasheets (Format) SEPS-5097 GDI-2964:

The equipment/subsystem Electrical ICD shall provi ... Y R

SEPS-5098 GDI-3440: ECSS-E-40 Part 1 section 5.2.2.1 (System requireme ...

Y

SEPS-5099 GDI-3441: ECSS-E-40 Part 1 section 5.2.2.2 (System and funct ...

Y

SEPS-5100 GDI-3442: ECSS-E-40 Part 1 section 5.2.3.1a (System design) ...

Y

SEPS-5101 GDI-3443: ECSS-E-40 Part 1 section 5.2.3.1b (System design t ...

Y


of 120




SEPS-5102 GDI-3444: ECSS-E-40 Part 1 section 5.2.3.1c ( System require ...

Y

SEPS-5103 GDI-3445: ECSS-E-40 Part 1 section 5.2.3.2a (Software-hardwa ...

Y

SEPS-5104 GDI-3446: ECSS-E-40 Part 1 section 5.2.3.2b (Traceability to ...

Y

SEPS-5105 GDI-3447: ECSS-E-40 Part 1 section 5.2.3.2c (System partitio ...

Y

SEPS-5106 GDI-3448: ECSS-E-40 Part 1 section 5.2.3.2d (System configur ...

Y

SEPS-5107 GDI-3449: ECSS-E-40 Part 1 section 5.2.4.2 (qualification en ...

Y

SEPS-5108 GDI-3450: ECSS-E-40 Part 1 section 5.2.4.3 (Software validat ...

Y

SEPS-5109 GDI-3451: ECSS-E-40 Part 1 section 5.2.4.4 (requirement base ...

Y

SEPS-5110 GDI-3452: ECSS-E-40 Part 1 section 5.2.4.5 (System Requireme ...

Y

SEPS-5111 GDI-3453: ECSS-E-40 Part 1 section 5.2.5.1a, b, c, d (Identi ...

Y

SEPS-5112 GDI-3454: ECSS-E-40 Part 1 section 5.2.5.2 (Control and data ...

Y

SEPS-5113 GDI-3455: ECSS-E-40 Part 1 section 5.2.5.3 (Data medium requ ...

Y

SEPS-5114 GDI-3456: ECSS-E-40 Part 1 section 5.2.5.4 (System database ...

Y

SEPS-5115 GDI-3457: ECSS-E-40 Part 1 section 5.2.5.5 (Identification o ...

Y


Y


Y

SEPS-5118 GDI-3460: ECSS-E-40 Part 1 section 5.2.5.9 (Planning of supp ...

Y

SEPS-5119 GDI-3461: ECSS-E-40 Part 1 section 5.2.6.1 (Phasing and mana ...

Y

SEPS-5120 GDI-3462: ECSS-E-40 Part 1 section 5.2.6.2 (System requireme ...

Y

SEPS-5121 GDI-3463: ECSS-E-40 Part 1 section 5.2.7.1 (Software mainten ...

Y

SEPS-5122 GDI-3464: ECSS-E-40 Part 1 section 5.2.7.2 (Definition of in ...

Y

SEPS-5123 GDI-3466: ECSS-E-40 Part 1 section 5.4.2.1 (Establishment an ...

Y

SEPS-5124 GDI-3467: ECSS-E-40 Part 1 section 5.4.2.1a (Software requir ...

Y

SEPS-5125 GDI-3468: ECSS-E-40 Part 1 section 5.4.2.1e (Software requir ...

Y

SEPS-5126 GDI-3469: ECSS-E-40 Part 1 section 5.4.2.1f (Software requir ...

Y

SEPS-5127 GDI-3470: ECSS-E-40 Part 1 section 5.4.2.2 (Definition of fu ...

Y


Y


of 120




SEPS-5129 GDI-3472: ECSS-E-40 Part 1 section 5.4.3.1 (Transformation o ...

Y

SEPS-5130 GDI-3473: ECSS-E-40 Part 1 section 5.4.3.2 (Software design ...

Y


Y

SEPS-5132 GDI-3475: ECSS-E-40 Part 1 section 5.4.3.4 (Software archite ...

Y


Y

SEPS-5134 GDI-3477: ECSS-E-40 Part 1 section 5.4.3.6 (Selection of a c ...

Y

SEPS-5135 GDI-3478: ECSS-E-40 Part 1 section 5.4.3.6a (Computational m ...

Y

SEPS-5136 GDI-3479: ECSS-E-40 Part 1 section 5.4.3.6b (Scheduling repo ...

Y

SEPS-5137 GDI-3480: ECSS-E-40 Part 1 section 5.4.3.7 (Description of s ...

Y

SEPS-5138 GDI-3481: ECSS-E-40 Part 1 section 5.4.3.8 (Development and ...

Y

SEPS-5139 GDI-3482: ECSS-E-40 Part 1 section 5.4.3.11 (Evaluation of r ...

Y

SEPS-5140 GDI-3483: ECSS-E-40 Part 1 section 5.4.3.12 (Analysis of pot ...

Y

SEPS-5141 GDI-3484: ECSS-E-40 Part 1 section 5.4.3.13 (Definition and ...

Y

SEPS-5142 GDI-3485: ECSS-E-40 Part 1 section 5.4.3.14 (Conducting a PD ...

Y

SEPS-5143 GDI-3487: ECSS-E-40 Part 1 section 5.5.2.1a,b,c (Detailed de ...

Y


Y

SEPS-5145 GDI-3489: ECSS-E-40 Part 1 section 5.5.2.3 (Production of so ...

Y

SEPS-5146 GDI-3490: ECSS-E-40 Part 1 section 5.5.2.4 (Utilisation of m ...

Y

SEPS-5147 GDI-3491: ECSS-E-40 Part 1 section 5.5.2.5 (Description of t ...

Y

SEPS-5148 GDI-3492: ECSS-E-40 Part 1 section 5.5.2.5a (Dynamic physica ...

Y

SEPS-5149 GDI-3493: ECSS-E-40 Part 1 section 5.5.2.5b (Scheduling simu ...

Y

SEPS-5150 GDI-3494: ECSS-E-40 Part 1 section 5.5.2.6 (Utilisation of d ...

Y

SEPS-5151 GDI-3495: ECSS-E-40 Part 1 section 5.5.2.7 (Determination of ...

Y


Y

SEPS-5153 GDI-3497: ECSS-E-40 Part 1 section 5.5.2.9 (Definition and d ...

Y

SEPS-5154 GDI-3498: ECSS-E-40 Part 1 section 5.5.2.10 (Updating of the ...

Y

SEPS-5155 GDI-3499: ECSS-E-40 Part 1 section 5.5.2.11 (Conducting a DD ...

Y


of 120





Y

SEPS-5157 GDI-3501: ECSS-E-40 Part 1 section 5.5.3.2 (Software unit te ...

Y

SEPS-5158 GDI-3502: ECSS-E-40 Part 1 section 5.5.3.3 (Software user ma ...

Y

SEPS-5159 GDI-3503: ECSS-E-40 Part 1 section 5.5.3.4 (Updating of the ...

Y

SEPS-5160 GDI-3504: ECSS-E-40 Part 1 section 5.5.4.1 (Software integra ...

Y

SEPS-5161 GDI-3505: ECSS-E-40 Part 1 section 5.5.4.2 (Software units a ...

Y

SEPS-5162 GDI-3506: ECSS-E-40 Part 1 section 5.5.4.3 (Software user ma ...

Y

SEPS-5163 GDI-3508: ECSS-E-40 Part 1 section 5.6.2.1 (Determination of ...

Y

SEPS-5164 GDI-3509: ECSS-E-40 Part 1 section 5.6.2.2 (Establishment of ...

Y

SEPS-5165 GDI-3510: ECSS-E-40 Part 1 section 5.6.2.2a (SW validation p ...

Y

SEPS-5166 GDI-3511: ECSS-E-40 Part 1 section 5.6.2.2b (SW validation p ...

Y

SEPS-5167 GDI-3512: ECSS-E-40 Part 1 section 5.6.2.3 (Selection of an ...

Y

SEPS-5168 GDI-3513: ECSS-E-40 Part 1 section 5.6.2.3a (ISVV validation ...

Y

SEPS-5169 GDI-3514: ECSS-E-40 Part 1 section 5.6.2.3b (ISVV validation ...

Y


Y


Y

SEPS-5172 GDI-3517: ECSS-E-40 Part 1 section 5.6.3.2a, b (Conducting t ...

Y

SEPS-5173 GDI-3518: ECSS-E-40 Part 1 section 5.6.3.3 (Updating the sof ...

Y

SEPS-5174 GDI-3519: ECSS-E-40 Part 1 section 5.6.3.4 (Test readiness r ...

Y

SEPS-5175 GDI-3520: ECSS-E-40 Part 1 section 5.6.3.5 (Conducting a CDR ...

Y


Y

SEPS-5177 GDI-3522: ECSS-E-40 Part 1 section 5.6.4.2a, b (Conducting t ...

Y

SEPS-5178 GDI-3523: ECSS-E-40 Part 1 section 5.6.4.3 (Updating the sof ...

Y

SEPS-5179 GDI-3524: ECSS-E-40 Part 1 section 5.6.4.4 (Test readiness r ...

Y

SEPS-5180 GDI-3525: ECSS-E-40 Part 1 section 5.6.4.5 (Conducting a QR ...

Y

SEPS-5181 GDI-3527: ECSS-E-40 Part 1 section 5.7.2.1 (Preparation of t ...

Y

SEPS-5182 GDI-3528: ECSS-E-40 Part 1 section 5.7.2.2 (Supplier's provi ...

Y


of 120




SEPS-5183 GDI-3529: ECSS-E-40 Part 1 section 5.7.2.3 (Installation pla ...

Y

SEPS-5184 GDI-3530: ECSS-E-40 Part 1 section 5.7.2.4a, b, c, d (Instal ...

Y

SEPS-5185 GDI-3531: ECSS-E-40 Part 1 section 5.7.3.1 (Acceptance test ...

Y

SEPS-5186 GDI-3532: ECSS-E-40 Part 1 section 5.7.3.2 (Acceptance test ...

Y

SEPS-5187 GDI-3533: ECSS-E-40 Part 1 section 5.7.3.3 (Executable code ...

Y

SEPS-5188 GDI-3534: ECSS-E-40 Part 1 section 5.7.3.4a (Supplier's supp ...

Y

SEPS-5189 GDI-3535: ECSS-E-40 Part 1 section 5.7.3.4b (Links with Soft ...

Y

SEPS-5190 GDI-3536: ECSS-E-40 Part 1 section 5.7.3.4c (Acceptance test ...

Y

SEPS-5191 GDI-3537: ECSS-E-40 Part 1 section 5.7.3.5 (Evaluation of ac ...

Y

SEPS-5192 GDI-3538: ECSS-E-40 Part 1 section 5.7.3.6a, b (Conducting a ...

Y

SEPS-5193 GDI-3540: ECSS-E-40 Part 1 section 5.8.2.1a, b, c (Determina ...

Y

SEPS-5194 GDI-3541: ECSS-E-40 Part 1 section 5.8.2.2a, b, c (Establish ...

Y

SEPS-5195 GDI-3542: ECSS-E-40 Part 1 section 5.8.2.3a, b (Selection of ...

Y


Y

SEPS-5197 GDI-3544: ECSS-E-40 Part 1 section 5.8.3.1 (Verification of ...

Y


Y


Y


Y


Y


Y


Y

SEPS-5204 GDI-3551: ECSS-E-40 Part 1 section 5.8.3.8 (verification of ...

Y

SEPS-5205 GDI-3552: ECSS-E-40 Part 1 section 5.8.3.9 (Evaluation of va ...

Y

SEPS-5206 GDI-3553: ECSS-E-40 Part 1 section 5.8.3.10a (problem and no ...

Y

SEPS-5207 GDI-3554: ECSS-E-40 Part 1 section 5.8.3.10b (problem and no ...

Y

SEPS-5208 GDI-3555: ECSS-E-40 Part 1 section 5.8.3.11a (Schedulability ...

Y

SEPS-5209 GDI-3556: ECSS-E-40 Part 1 section 5.8.3.11b (Schedulability ...

Y


of 120




SEPS-5210 GDI-3557: ECSS-E-40 Part 1 section 5.8.3.11c (Schedulability ...

Y


Y


Y

SEPS-5213 GDI-3560: ECSS-E-40 Part 1 section 5.8.3.12c (Schedulability ...

Y


Y


Y


Y

SEPS-5217 GDI-3565: ECSS-E-40 Part 1 section 5.3.2.1 (Definition of so ...

Y

SEPS-5218 GDI-3566: ECSS-E-40 Part 1 section 5.3.2.2a (Software life c ...

Y

SEPS-5219 GDI-3567: ECSS-E-40 Part 1 section 5.3.2.2b (Software life c ...

Y

SEPS-5220 GDI-3568: ECSS-E-40 Part 1 section 5.3.2.2c (Software life c ...

Y


Y


Y


Y

SEPS-5224 GDI-3572: ECSS-E-40 Part 1 section 5.3.2.6 (Requirements bas ...

Y

SEPS-5225 GDI-3573: ECSS-E-40 Part 1 section 5.3.2.7 (Software technic ...

Y

SEPS-5226 GDI-3574: ECSS-E-40 Part 1 section 5.3.2.8 (PDR - Preliminar ...

Y

SEPS-5227 GDI-3575: ECSS-E-40 Part 1 section 5.3.2.9 (DDR - detailed d ...

Y

SEPS-5228 GDI-3576: ECSS-E-40 Part 1 section 5.3.2.10a (CDR - Critical ...

Y

SEPS-5229 GDI-3577: ECSS-E-40 Part 1 section 5.3.2.10b (CDR - Critical ...

Y

SEPS-5230 GDI-3578: ECSS-E-40 Part 1 section 5.3.2.11 (software verifi ...

Y

SEPS-5231 GDI-3579: ECSS-E-40 Part 1 section 5.3.2.12a (QR - Qualifica ...

Y

SEPS-5232 GDI-3580: ECSS-E-40 Part 1 section 5.3.2.12b (QR/Review of s ...

Y

SEPS-5233 GDI-3581: ECSS-E-40 Part 1 section 5.3.2.13 (AR - Acceptance ...

Y

SEPS-5234 GDI-3582: ECSS-E-40 Part 1 section 5.3.2.14 (Validation acti ...

Y

SEPS-5235 GDI-3583: ECSS-E-40 Part 1 section 5.3.2.15 (Software procur ...

Y

SEPS-5236 GDI-3584: ECSS-E-40 Part 1 section 5.3.3.2a, b, c (Support t ...

Y


of 120




SEPS-5237 GDI-3585: ECSS-E-40 Part 1 section 5.3.3.3a (Technical revie ...

Y

SEPS-5238 GDI-3586: ECSS-E-40 Part 1 section 5.3.3.3b (Technical revie ...

Y

SEPS-5239 GDI-3587: ECSS-E-40 Part 1 section 5.3.4.1 (Interface defini ...

Y

SEPS-5240 GDI-3588: ECSS-E-40 Part 1 section 5.3.4.2 Interface managem ...

Y

SEPS-5241 GDI-3589: ECSS-E-40 Part 1 section 5.3.5.1 (Technical budget ...

Y

SEPS-5242 GDI-3590: ECSS-E-40 Part 1 section 5.3.5.2 (Technical budget ...

Y


of 120



9 EMC APPLICABILITY MATRIX







SEPS-6146 EMC-545: Class "R" Bonds shall be made by direct metal to m ...

Y R

SEPS-6147 EMC-529: The contact surface area of the two items to be bo ...

Y R

SEPS-6148 EMC-530: Class R bonds shall be assembled so that a DC resi ...

Y T

SEPS-6149 EMC-735: Class "R" bonds shall be verified in both directio ...

Y T

SEPS-6150 EMC-531: Where bond straps are required for class R bond pu ...

Y A

SEPS-6151 EMC-532: The bond shall have an adequate cross section to c ...

Y A

SEPS-6152 EMC-536: Bonding of metallic surfaces shall be made by meta ...

Y R

SEPS-6153 EMC-537: The assembled class S bond (i.e. metallic strap / ...

Y T

SEPS-6154 EMC-553: Bonding for powered equipment not requiring a zero ...

Y T

SEPS-6155 EMC-554: The bond assembly shall be sized to carry 150% of ...

Y A

SEPS-6156 EMC-388: Joint faces shall be flat and clean before assembl ...

Y I,R

SEPS-6157 EMC-559: To prevent corrosion and alloying, bonding of elec ...

Y A

SEPS-6158 EMC-560: Where dissimilar materials are to be bonded, the r ...

Y A

SEPS-6159 EMC-669: A suitable anti-corrosion coating shall be applied ...

Y R

SEPS-6160 EMC-859: Conformance to electrical bonding requirements sha ...

Y R

SEPS-6161 EMC-398: Structural elements including connector brackets, ...

Y T,R

SEPS-6162 EMC-645: All housing parts, including connector recepticles ...

Y T

SEPS-6163 EMC-644: Across Movable parts, a bond strap shall be applie ...

Y T

SEPS-6164 EMC-406: Mechanical Parts without electrical nor shielding ...

Y T,R

SEPS-6165 EMC-592: Conductive structural elements which form part of ...

Y T,R

SEPS-6166 EMC-407: Mechanical Parts used for electromagnetic shieldin ...

Y T,R

SEPS-6167 EMC-693: The cable harness overall shield is considered to ...

Y R


of 120




SEPS-6168 EMC-694: A long the harness length the average distance bet ...

Y T,R

SEPS-6169 EMC-677: The BepiColumbo Grounding Concept shall be governe ...

Y A,R

SEPS-6170 EMC-683: The concept shall be implemented through the use o ...

Y R

SEPS-6171 EMC-687: The location of this point shall be chosen so as t ...

Y A,R

SEPS-6172 EMC-688: Interconnection of the dedicated ground reference ...

Y R

SEPS-6173 EMC-705: The distributed prime power shall not be utilised ...

Y R

SEPS-6174 EMC-703: The Ground Reference for the generated secondary V ...

Y T

SEPS-6175 EMC-437: Grounding: All secondary power supplies, inside a ...

Y I,R

SEPS-6176 EMC-439: Power distributed between units (1 supplier; 1 rec ...

Y R

SEPS-6177 EMC-440: Power distributed between units (1 supplier; sever ...

Y R

SEPS-6178 EMC-719: Specific care shall be taken to avoid grounding lo ...

Y R

SEPS-6179 EMC-441: After grounding, the impedance between the unit se ...

Y T

SEPS-6180 EMC-438: Isolation: Prior to connection of the unit interna ...

Y T,R

SEPS-6181 EMC-724: The high level voltages, both positive and negativ ...

Y T

SEPS-6182 EMC-725: The location of the secondary reference point shal ...

Y R

SEPS-6183 EMC-445: Grounding of signal circuits interfacing between S ...

Y R

SEPS-6184 EMC-446: Where single-ended signal transmitters are used, i ...

Y R

SEPS-6185 EMC-447: The use of common signal return paths is to be dis ...

Y R

SEPS-6186 EMC-721: With the exception of declared Rf signals the use ...

Y R

SEPS-6187 EMC-726: Interface circuits (with the exception of selected ...

Y T

SEPS-6188 EMC-410: Each unit shall provide a grounding point, which i ...

Y I

SEPS-6189 EMC-415: All units shall have a M4 bonding stud ...

Y I

SEPS-6190 EMC-417: The resistance between the bonding stud and the un ...

Y T

SEPS-6191 EMC-442: A grounding diagram showing the implementation of ...

Y I

SEPS-6192 EMC-727: The minimum content of each grounding diagram shal ...

Y I

SEPS-6193 EMC-1328: The symbols shown in figure EMC-1347 below shall b ...

Y R

SEPS-6194 EMC-449: EGSE signal and power circuits interfacing with fl ...

Y R


of 120




SEPS-6195 EMC-411: CFRP and SiC shall not be used as an electrical bo ...

Y R

SEPS-6196 EMC-419: Space exposed Insulating material having a surface ...

Y R

SEPS-6197 EMC-425: PAINTS: Refer to PA Section above. ...

Y R

SEPS-6198 EMC-426: HEATERS & THERMISTORS: Heaters, thermistors and o ...

Y T,R

SEPS-6199 EMC-413: The structure of electrical and electronic units s ...

Y T

SEPS-6200 EMC-697: Distances between screws for lids, etc... shall ne ...

Y R

SEPS-6201 EMC-414: Discontinuities e.g. openings for ventilation, dra ...

Y A,I

SEPS-6202 EMC-708: All harness and associated backshells shall form a ...

Y T,I

SEPS-6203 EMC-891: Thermal hardware e.g. thermocouples and heatermats ...

Y R

SEPS-6204 EMC-714: The electrical wiring harness shall be separated i ...

Y R

SEPS-6205 EMC-715: The cables of each harness type shall be routed as ...

Y R

SEPS-6206 EMC-885: Cable bundles shall be separated by at least 5cm w ...

Y R

SEPS-6207 EMC-888: Test harness and connection access shall be config ...

Y R

SEPS-6208 EMC-889: Thermal harness used during flight shall be catego ...

Y R

SEPS-6209 EMC-716: Cable and shield shall be considered for each sign ...

Y R

SEPS-6210 EMC-883: Each harness bundle shall have an overall shield o ...

Y I,R

SEPS-6211 EMC-884: All cable shields shall be grounded at both ends, ...

Y T

SEPS-6212 EMC-717: Use in preference order: MIL Round with approv ...

Y R

SEPS-6213 EMC-1330: Shield termination at connectors shall be as shown ...

Y R

SEPS-6214 EMC-803: Electromagnetic interference safety margins are ma ...

Y A

SEPS-6215 EMC-804: A minimum acceptable safety margin is to be achiev ...

Y T,A

SEPS-6216 EMC-815: All electronic and electrical items whose performa ...

Y R

SEPS-6217 EMC-816: Isolated conducting items subject to energetic ele ...

Y R

SEPS-6218 EMC-818: A controlled grounding and isolation concept has b ...

Y R

SEPS-6219 EMC-801: The EMC Programme is controlled and documented by ...

Y R

SEPS-6220 EMC-842: The submitted EMC Contol Plan shall co-ordinate th ...

Y R


of 120




SEPS-6221 EMC-730: Each power line interface shall be designed to be ...

Y R

SEPS-6222 EMC-731: Each power user shall ensure that: at electrical c ...

Y T

SEPS-6223 EMC-455: For 28V busses inrush current at unit switch on sh ...

Y T

SEPS-6224 EMC-457: For 28V: The transient on the primary power bus di ...

Y T

SEPS-6225 EMC-459: For 28V: Conducted voltage transients on the prima ...

Y T

SEPS-6226 EMC-453: The Conducted Emission requirements given below ar ...

Y R

SEPS-6227 EMC-461: Conducted narrow band current emissions (different ...

Y T

SEPS-6228 EMC-463: Conducted narrow band current emissions (common mo ...

Y T

SEPS-6229 EMC-465: In case of internal redundancy, conducted emission ...

Y T

SEPS-6230 EMC-467: Differential Mode: Time domain conducted current r ...

Y T

SEPS-6231 EMC-893: Time domain conducted voltage ripple/spike on the ...

Y T

SEPS-6232 EMC-468: Common Mode: The time domain conducted current ri ...

Y T

SEPS-6233 EMC-469: In case of internal redundancy, time domain emissi ...

Y T

SEPS-6234 EMC-473: The maximum voltage emission levels for secondary ...

Y T

SEPS-6235 EMC-475: The voltage ripple and spikes on secondary power s ...

Y T

SEPS-6236 EMC-464: Frequency Domain: Conducted narrow band (NB) curre ...

Y T

SEPS-6237 EMC-481: Primary power bus powered units shall not exhibit ...

Y T

SEPS-6238 EMC-483: Primary power bus powered units shall not exhibit ...

Y T

SEPS-6239 EMC-485: The unit shall not exhibit any failures, malfuncti ...

Y T

SEPS-6240 EMC-490: When secondary lines power a unit, the unit shall ...

Y T

SEPS-6241 EMC-491: When a unit delivers secondary power, the unit sha ...

Y T

SEPS-6242 EMC-493: The conducted susceptibility specification for sec ...

Y T,R

SEPS-6243 EMC-495: In addition, a margin of at least +6dB shall be de ...

Y T,R

SEPS-6244 EMC-927: Reciever circiuts shall not respond to the followi ...

Y

SEPS-6245 EMC-497: The unit shall not exceed the limits of figure EMC ...

Y T,A


of 120




SEPS-6246 EMC-502: The Radiated H field generated by Units, shall not ...

Y T

SEPS-6247 EMC-1342: Unit low frequency AC test requirements to achieve ...

Y T

SEPS-6248 EMC-505: The unit shall not show any malfunction or deviati ...

Y T

SEPS-6249 EMC-506: The unit shall not show any malfunction or deviati ...

Y T

SEPS-6250 EMC-510: Units shall not show any malfunction or deviation ...

Y A

SEPS-6251 EMC-514: The use of ferro-magnetics shall be avoided for pa ...

Y I,R

SEPS-6252 EMC-516: Steel or other magnetic materials shall be avoided ...

Y T,I,R

SEPS-6253 EMC-517: It is not permitted to use high permeable shieldin ...

Y

SEPS-6254 EMC-518: The use of relays shall be limited to the most cri ...

Y R

SEPS-6255 EMC-519: The maximum magnetic moment applicable to each uni ...

Y R

SEPS-6256 EMC-522: The unit shall not be susceptible when submitted t ...

Y T

SEPS-6257 EMC-323: MGSE shall not interfere with the aims of Electric ...

Y R

SEPS-6258 EMC-306: All MGSE used for test purposes shall provide bond ...

Y R

SEPS-6259 EMC-298: All MGSE used for electrical tests shall provide g ...

Y R

SEPS-6260 EMC-308: All electromechanical devices with a safety wire c ...

Y R

SEPS-6261 EMC-310: Transport containers and protective covers for the ...

Y R

SEPS-6262 EMC-314: EGSE shall not interfere with the aims of Electric ...

Y R

SEPS-6263 EMC-325: EMI orginated by EGSE shall be limited to such ext ...

Y T,R

SEPS-6264 EMC-320: The Bonding, Grounding and Isolation of all EGSE s ...

Y R

SEPS-6265 EMC-331: Each EGSE shall include a mains isolation transfor ...

Y I

SEPS-6266 EMC-332: Compliance to EN 60335-1 Class II ...

Y

SEPS-6267 EMC-333: Provide galvanic isolation from the supplied Phase ...

Y T

SEPS-6268 EMC-334: Provide galvanic isolation from the Industrial sup ...

Y T

SEPS-6269 EMC-336: Provide a ground reference point for the isolated ...

Y T

SEPS-6270 EMC-338: Provide adequate safety protection devices (See di ...

Y T

SEPS-6271 EMC-382: Provide adequate Powerline filtering to ensure tha ...

Y T

SEPS-6272 EMC-335: Ensure an isolation value of at least 4 kV primar ...

Y T


of 120




SEPS-6273 EMC-339: Power (ac & dc) shall be distributed within the EG ...

Y T

SEPS-6274 EMC-370: The loss of any powerline shall not cause damage t ...

Y T

SEPS-6275 EMC-371: Subsequent restoration of power either partially o ...

Y T

SEPS-6276 EMC-372: Uninterruptable power supplies may be used only wi ...

Y R

SEPS-6277 EMC-341: Each EGSE shall provide an internal ground referen ...

Y R

SEPS-6278 EMC-342: Each EGSE rack/unit tester shall provide a bonding ...

Y T

SEPS-6279 EMC-343: The EGSE rack housing shall be bonded to the inter ...

Y T

SEPS-6280 EMC-344: The bonding stud shall be connected to the EGSE gr ...

Y T

SEPS-6281 EMC-361: EGSE comprising more than one rack (e.g. at Instru ...

Y T

SEPS-6282 EMC-351: EGSE signal/power circuits interfacing with onboar ...

Y T

SEPS-6283 EMC-354: The signal interfaces between onboard hardware and ...

Y T

SEPS-6284 EMC-352: EGSE buffer and isolation circuitry and associated ...

Y T

SEPS-6285 EMC-353: Additional line drivers in the cable harness betwe ...

Y T

SEPS-6286 EMC-358: The grounding of shields on interface circuits wit ...

Y T

SEPS-6287 EMC-360: Signals/interfaces requiring connection to onboard ...

Y T

SEPS-6288 EMC-376: All EGSE shall provide adequate AC power line inpu ...

Y T,A

SEPS-6289 EMC-377: EGSE units/racks shall not compromise other EGSE w ...

Y

SEPS-6290 EMC-374: All EGSE shall maintain a conducted margin of at l ...

Y T,A

SEPS-6291 EMC-378: EGSE housing/racks shall be RF tight to the maximu ...

Y T,R

SEPS-6292 EMC-379: No EGSE shall compromise the objective of EMC and ...

Y T,A

SEPS-6293 EMC-380: EGSE located within the anechoic chamber during an ...

Y T,A

SEPS-6294 EMC-348: For each EGSE /EGSE set-up a grounding diagram sha ...

Y R

SEPS-6295 EMC-169: All EMC tests shall be conducted under standard am ...

Y R

SEPS-6296 EMC-171: The test facilities used for the EMC test program ...

Y R

SEPS-6297 EMC-174: The maximum allowable tolerance for the test param ...

Y R

SEPS-6298 EMC-176: The accuracy of measurement equipment and test equ ...

Y R


of 120




SEPS-6299 EMC-178: Grounding of Test Equipment: Measurement equipment ...

Y R

SEPS-6300 EMC-179: Antenna Placement: For radiated emission measureme ...

Y R

SEPS-6301 EMC-180: Receiver Bandwidth: The following receiver bandwid ...

Y R

SEPS-6302 EMC-182: Power Adjustment: The primary power for unit/equip ...

Y R

SEPS-6303 EMC-184: For the conducted emission and susceptibility test ...

Y R

SEPS-6304 EMC-187: Each LISN has to be designed and provided by the c ...

Y T

SEPS-6305 EMC-191: These particular tests shall demonstrate the compl ...

Y R

SEPS-6306 EMC-192: The equipment under test shall be switched on in t ...

Y R

SEPS-6307 EMC-193: For emission testing the unit/equipment shall oper ...

Y R

SEPS-6308 EMC-194: For susceptibility testing the suitable operationa ...

Y R

SEPS-6309 EMC-195: After testing the equipment shall be switched off ...

Y R

SEPS-6310 EMC-196: Both Emission and Susceptibility operational test ...

Y R

SEPS-6311 EMC-197: The particular test set-up shall represent the fli ...

Y R

SEPS-6312 EMC-199: General Aspects: Each item (from unit/equipment to ...

Y R

SEPS-6313 EMC-200: Data Acquisition: The item under test shall be con ...

Y R

SEPS-6314 EMC-203: This test shall verify the DC resistance of bondin ...

Y R

SEPS-6315 EMC-204: The bonding test shall be performed with the unit/ ...

Y R

SEPS-6316 EMC-205: The bonding test shall be performed without any ha ...

Y R

SEPS-6317 EMC-863: Milliohm level bonds imposed for RF interference c ...

Y T

SEPS-6318 EMC-865: All elements that could discharge, were they isola ...

Y T

SEPS-6319 EMC-866: Immunity to electrostatic discharge shall be verif ...

Y T

SEPS-6320 EMC-868: Control of static charging, plasma/payload induced ...

Y T,A

SEPS-6321 EMC-207: This test is to measure the isolation of primary a ...

Y R

SEPS-6322 EMC-208: The isolation test shall be performed with the UUT ...

Y R


of 120




SEPS-6323 EMC-212: This test shall demonstrate the compliance of the ...

Y R

SEPS-6324 EMC-213: UUT operation shall be selected in order to maximi ...

Y R

SEPS-6325 EMC-215: Ripple and transient interference tests on the pow ...

Y R

SEPS-6326 EMC-219: This test shall measure the conducted emissions (r ...

Y R


Y R

SEPS-6328 EMC-221: When the secondary power provider and user need to ...

Y R


Y T

SEPS-6330 EMC-229: This test shall demonstrate the noise immunit/equi ...

Y R

SEPS-6331 EMC-230: The mode selection for susceptibility testing shal ...

Y R

SEPS-6332 EMC-238: This test shall demonstrate the noise immunit/equi ...

Y R

SEPS-6333 EMC-239: The mode selection for susceptibility testing shal ...

Y R


Y R


Y R

SEPS-6336 EMC-252: This test shall demonstrate the immunity of the te ...

Y R


Y R

SEPS-6338 EMC-256: This test shall demonstrate the immunit/equipmenty ...

Y R


Y R

SEPS-6340 EMC-260: The ESD test, radiated discharges, shall demonstra ...

Y R


Y R

SEPS-6342 EMC-265: This test shall be used in order to show the compl ...

Y T,R

SEPS-6343 EMC-267: Verification by similarity may be applied to units ...

Y A,R


of 120



10 ENVIROMENT AND TEST APPLICABILITY MATRIX







SEPS-6346 ET-14273: The MCS coordinate system is shown below. The +Y a ...

Y R

SEPS-6347 ET-36: Sine and random vibrations: The following mechanic ...

Y A,R

SEPS-6348 ET-15090: Sinus Environment during Road Trans ...

Y A,R

SEPS-6349 ET-15091: Random Virbation Environment during ...

Y A,R

SEPS-6350 ET-15092: Standard Sinus environment during A ...

Y A,R

SEPS-6351 ET-15094: Antonov 124 specific quasi-static l ...

Y A,R

SEPS-6352 ET-15095: Antonov 124 specific crash load las ...

Y A,R

SEPS-6353 ET-15096: Antonov 124 specific sinus vibratio ...

Y A,R

SEPS-6354 ET-15098: The LV generated quasi-staic loads at satellite Co ...

Y A

SEPS-6355 ET-15100: The LV generated sine vibration loads at the LV-Ad ...

Y A

SEPS-6356 ET-15102: The LV generated random vibration loads at the LV- ...

Y A

SEPS-6357 ET-210: System level sine vibration inputs.

Y T,A

SEPS-6358 ET-212: Acoustic test spectra...

Y T,A

SEPS-6359 ET-215: Shock environment of separation eve ...

Y T

SEPS-6360 ET-216: A low frequency rectangular shock pulse with a dur ...

Y A,R

SEPS-6361 ET-15106: The following accelerations shall be considered du ...

Y A

SEPS-6362 ET-14642: For external items the heatexchange and absorbed f ...

Y A


of 120




SEPS-6363 ET-160: A generic unit/equipment/subsystem temperature lev ...

Y T,A,R

SEPS-6364 ET-14757: For MTM units, the following temperature limits ap ...

Y T,A

SEPS-6365 ET-14785: Propulsion Temperature limits (design temperatures ...

Y T,A

SEPS-6366 ET-249: All equipment shall be designed to withstand a rel ...

Y R

SEPS-6367 ET-252: For AIV and storage, all equipment shall withstand ...

Y R

SEPS-6368 ET-253: During transport prior to integration on the space ...

Y R

SEPS-6369 ET-254: The flight hardware transportation containers shal ...

Y R

SEPS-6370 ET-14284: For thermal analyses of orbiting spacecraft, in or ...

Y A,R

SEPS-6371 ET-14288: The solar electromagnetic radiation includes infra ...

Y R

SEPS-6372 ET-14287: In most of thermal applications, the solar spectru ...

Y R

SEPS-6373 ET-14632: After encapsulation under the fairing, the spacecr ...

Y

SEPS-6374 ET-14635: The typical mission timeline for BC is shown in ta ...

Y A

SEPS-6375 ET-427: The nominal Solar constant in earth orbit is 1370 ...

Y A

SEPS-6376 ET-429: The albedo factor is the ratio between the solar p ...

Y A

SEPS-6377 ET-430: For short averaging time (t < 0.3 hr), the followi ...

Y A

SEPS-6378 ET-431: The Earth and its atmosphere emit an infra-red rad ...

Y A

SEPS-6379 ET-251: Units mounted on the S/C shall be designed to with ...

Y A,R

SEPS-6380 ET-14628: The thermal flux density radiated by the fairing o ...

Y A

SEPS-6381 ET-14626: The aerothermal flux after fairing jettison of 113 ...

Y A

SEPS-6382 ET-14634: The spacecraft attitude during LEOP shall be consi ...

Y A

SEPS-6383 ET-432: The thermal design shall allow lunar and earth ecl ...

Y A

SEPS-6384 ET-428: The maximum spacecraft to sun distance shall be 1. ...

Y A

SEPS-6385 ET-461: Solar and Planetary Electromagnetic Radiation ...

Y R

SEPS-6386 ET-462: Neutral Atmosphere ...

Y R

SEPS-6387 ET-463: Plasmas ...

Y R

SEPS-6388 ET-464: Energetic Particle Radiation ...

Y R

SEPS-6389 ET-466: Contamination ...

Y R


of 120




SEPS-6390 ET-467: Thermal (described in section 5) ...

Y R

SEPS-6391 ET-15264: For many of the associated analyses it is necessar ...

Y A

SEPS-6392 ET-14252: Average and worst case irradiance levels for the h ...

Y A

SEPS-6393 ET-15112: The Table below gives the parameters which shall b ...

Y R

SEPS-6394 ET-15299: For trapped radiation source term evaluation withi ...

Y A

SEPS-6395 ET-15303: For solar particle events (solar protons) the refe ...

Y A

SEPS-6396 ET-15302: To predict the fluences seen by BepiColombo an inv ...

Y A

SEPS-6397 ET-15304: For analysing single event upset rates during sola ...

Y A

SEPS-6398 ET-15306: CREME96 shall be the standard model for cosmic ray ...

Y A

SEPS-6399 ET-15308: It is possible to make upset rate predictions only ...

Y A

SEPS-6400 ET-15309: The CREME96 method shall be used [13], [14] for th ...

Y A

SEPS-6401 ET-15310: The test data shall show the normalised upset rate ...

Y A

SEPS-6402 ET-15312: The EQFRUX-Si or EQFRUX-Ga models shall be used fo ...

Y A

SEPS-6403 ET-15314: Secondary radiation has to be analysed on a case-b ...

Y A

SEPS-6404 ET-15316: The ionizing dose environment is represented by th ...

Y A

SEPS-6405 ET-15323: The solar proton spectrum which shall be applied f ...

Y A

SEPS-6406 ET-15327: The galactic cosmic ray (GCR) LET spectrum which ...

Y A

SEPS-6407 ET-15330: The BC spacecraft MCS elements shall be able to sa ...

Y A

SEPS-6408 ET-15331: Peak fluxes (worst week, worst day, peak 5 minutes ...

Y A

SEPS-6409 ET-15334: The source term of electrons at 0.39 AU shown in F ...

Y A

SEPS-6410 ET-15339: The BC MCS elements shall withstand the effects of ...

Y A

SEPS-6411 ET-15356: Table ET-15358 lists the types of testing which sh ...

Y T,R

SEPS-6412 ET-14302: Contamination and cleanliness requirements are add ...

Y R

SEPS-6413 ET-15038: ECSS-E-10-03A shall apply with the modifications d ...

Y

SEPS-6414 ET-105: Qualification of the design shall be accomplished ...

Y R

SEPS-6415 ET-14256: The objective of the qualification shall be to dem ...

Y T,A

SEPS-6416 ET-14258: The test specimen shall be subjected to qualificat ...

Y T


of 120




SEPS-6417 ET-14259: The test conditions shall not exceed design margin ...

Y T,R

SEPS-6418 ET-14260: Items which can be qualified by an applicable qual ...

Y T,R

SEPS-6419 ET-14261: Qualification testing shall be conducted at the re ...

Y R

SEPS-6420 ET-107: Environmental acceptance testing shall be performe ...

Y T

SEPS-6421 ET-14263: During environmental acceptance testing, condition ...

Y T

SEPS-6422 ET-109: The objective of the test item functional performa ...

Y T,A

SEPS-6423 ET-14265: An initial and a final functional performance test ...

Y T

SEPS-6424 ET-14266: Intermediate functional performance tests, which m ...

Y T

SEPS-6425 ET-14267: A functional performance test may run continuously ...

Y T

SEPS-6426 ET-14268: The test shall be conducted under standard laborat ...

Y R

SEPS-6427 ET-14269: The tests shall be performed in compliance with ap ...

Y T

SEPS-6428 ET-14270: Failure detection, isolation and recovery function ...

Y T

SEPS-6429 ET-14271: Functional test will be performed by operating all ...

Y T

SEPS-6430 ET-111: Any test facility to be used within the instrument ...

Y A,R

SEPS-6431 ET-113: The accuracy of instrument and test equipment used ...

Y A,R

SEPS-6432 ET-115: The allowed test condition tolerances shall be app ...

Y A,I,R

SEPS-6433 ET-119: Unless otherwise specified herein, all measurement ...

Y A,I,R

SEPS-6434 ET-14276: The cleanliness requirements for the test items du ...

Y A,I,R

SEPS-6435 ET-121: Test execution shall be started only if all starti ...

Y A,I,R

SEPS-6436 ET-14277: Prior to and after every environmental test activi ...

Y I

SEPS-6437 ET-14279: Before commencing any formal qualification or acce ...

Y R

SEPS-6438 ET-14278: After completion of all formal qualifications or a ...

Y R

SEPS-6439 ET-123: The test is successfully performed if all measurem ...

Y T,A

SEPS-6440 ET-14280: Modifications, repair, replacement or refurbishmen ...

Y T,A

SEPS-6441 ET-127: The unit/equipment/subsystem under test shall be m ...

Y T

SEPS-6442 ET-128: At least one triaxial sensor shall be mounted on t ...

Y T

SEPS-6443 ET-129: At least two axis aligned sensors shall be mounted ...

Y T


of 120




SEPS-6444 ET-130: All unit/equipment/subsystems powered on during la ...

Y T

SEPS-6445 ET-15033: Any need for notching shall be notified to ASD as ...

Y T,A

SEPS-6446 ET-133: The test item shall be attached to the vibration e ...

Y T

SEPS-6447 ET-134: The variation of transmissibility between test ite ...

Y T

SEPS-6448 ET-135: Adequate fixture design and specimen installation ...

Y T

SEPS-6449 ET-136: A pre-test of the empty fixture shall be performed ...

Y T

SEPS-6450 ET-202: In case of large and heavy test items (e.g. module ...

Y

SEPS-6451 ET-203: Proof testing of test adapters is specified in the ...

Y T

SEPS-6452 ET-138: Frequency search tests shall be conducted in order ...

Y T

SEPS-6453 ET-140: Frequency search tests shall be conducted along ea ...

Y T

SEPS-6454 ET-14312: Units mounted on the spacecraft shall be designed ...

Y T,A

SEPS-6455 ET-14391: Units mounted on the spacecraft shall be designed ...

Y T,A

SEPS-6456 ET-14434: After freeze of unit accommodation the loads as de ...

Y R

SEPS-6457 ET-14590: Units shall be designed and tested to withstand wi ...

Y T,A,R

SEPS-6458 ET-149: Sine and random vibration tests shall be performed ...

Y T

SEPS-6459 ET-150: Prior and after sine and random vibration qualific ...

Y T

SEPS-6460 ET-151: Before applying full levels, a test at intermediat ...

Y T

SEPS-6461 ET-152: Any notching must be formally requested as a waive ...

Y T

SEPS-6462 ET-153: The vibration facility shall include a shock free ...

Y T

SEPS-6463 ET-155: Unit/equipment/subsystems shall demonstrate by tes ...

Y T

SEPS-6464 ET-156: Prior and after shock tests a low level sine frequ ...

Y T

SEPS-6465 ET-14624: Shock testing shall be performed with a device pr ...

Y T

SEPS-6466 ET-14625: The qualification to shock has to be demonstrated ...

Y T

SEPS-6467 ET-158: Static tests shall be performed by applying static ...

Y T

SEPS-6468 ET-15044: For sealed or pressurized equipments, pressure and ...

Y

SEPS-6469 ET-230: All units/equipments exposed to solar illumination ...

Y T,R

SEPS-6470 ET-231: The following temperature margins shall be taken f ...

Y T


of 120




SEPS-6471 ET-162: The temperatures shall be selected and controlled ...

Y R

SEPS-6472 ET-163: The test arrangement shall be as shown in Figure E ...

Y R

SEPS-6473 ET-164: The unit/equipment/subsystem shall be bolted to a ...

Y R

SEPS-6474 ET-165: On all external surfaces flight representative the ...

Y R

SEPS-6475 ET-166: The heat sink (HS) plates shall be black painted ( ...

Y R

SEPS-6476 ET-167: The conductive heat sink temperature and the chamb ...

Y R

SEPS-6477 ET-168: For vacuum tests the pressure inside the chamber s ...

Y R

SEPS-6478 ET-172: unit/equipment/subsystem’s suppliers shall perform ...

Y T

SEPS-6479 ET-174: The TV test on unit/equipment/subsystem level shal ...

Y R

SEPS-6480 ET-176: The unit/equipment/subsystems shall be tested foll ...

Y T,R

SEPS-6481 ET-182: unit/equipment/subsystem suppliers shall perform t ...

Y T

SEPS-6482 ET-183: The thermal vacuum acceptance test shall be perfor ...

Y T,R

SEPS-6483 ET-187: unit/equipment/subsystem suppliers shall perform t ...

Y T

SEPS-6484 ET-188: The thermal vacuum protoflight test shall be perfo ...

Y T,R

SEPS-6485 ET-191: With regard to radiation testing the manufacturer ...

Y R

SEPS-6486 ET-193: With regard to unit/equipment/subsystem EMC testin ...

Y R

SEPS-6487 ET-15042: With regard to unit/equipment/subsystem ESD testin ...

Y R

SEPS-6488 ET-195: A life test shall be required for all the assembli ...

Y T,R

SEPS-6489 ET-197: Space conditioning shall be performed whenever des ...

Y T,R

SEPS-6490 ET-198: The contractors shall propose the corresponding te ...

Y R

SEPS-6491 ET-199: For example, but without limitation to, materials ...

Y T

11.1 SCOPE 11.2 Mechanical Test Objectives 11.3 Notching Pilosophy 11.4 Essential Rules 11.5 Notching Sine Test Spectrum 11.6 Notching Random Test Spectrum 11.6.1 General Notching Criteria 11.6.2 Detailed Notching Criteria 11.6.2.1 Notching of a single resonance 11.6.2.2 Notching of a multi DOF equipment 11.6.2.3 Combined interface loads 11.6.3 Notching during tests


of 120




11.6.3.1 Identification of eigen modes 11.6.3.2 Determination of the interface loads 11.6.3.3 Determination of the notched spectrum 11.6.3.4 Random Tests at intermediate levels 11.6.3.5 Measurement plan 11.7 Random notching example


of 120



11 OPERATIONAL AND AUTONOMY APPLICABILITY MATRIX

The following table lists the applicable requirements of the OPA

It contains, in the first column, the Local ID for each applicable OPA requirement number.

The second column contains the OPA Requirement number and the opening text of the requirement.




SEPS-6887 OPA-2090: The following documents, of the latest issue, or o ...

Y R

SEPS-6888 OPA-1823: The spacecraft shall provide visibility of its int ...

Y T,R

SEPS-6889 OPA-1824: The control functions (telecommands) provided at e ...

Y T,R

SEPS-6890 OPA-1830: The spacecraft shall not require any TM monitoring ...

Y R

SEPS-6891 OPA-59: During all mission phases there shall be no requir ...

Y R

SEPS-6892 OPA-60: Situations in which the Ground is expected to reac ...

Y R

SEPS-6893 OPA-61: Situations in which the Ground is required to reac ...

Y R

SEPS-6894 OPA-62: Autonomous recovery to normal operations after a r ...

Y R

SEPS-6895 OPA-63: The spacecraft shall be able to continue nominal o ...

Y A

SEPS-6896 OPA-67: The spacecraft shall always be able to receive and ...

Y T,R

SEPS-6897 OPA-2051: It shall be possible to evaluate the consumed prop ...

Y A

SEPS-6898 OPA-71: The modes of the spacecraft and its payload, subsy ...

Y R

SEPS-6512 OPA-1099: For his contribution the sub-contractor shall iden ...

Y R

SEPS-6513 OPA-1108: After being powered-up, each equipment/subsystem s ...

Y T

SEPS-6899 OPA-72: The telemetry shall provide unambiguous identifica ...

Y R

SEPS-6514 OPA-1101: The sub-contractor shall identify all internal and ...

Y T

SEPS-6900 OPA-73: The spacecraft shall be able to support the modes ...

Y T

SEPS-6901 OPA-74: Initialisation of a mode (at spacecraft, subsystem ...

Y T

SEPS-6902 OPA-75: The spacecraft shall autonomously prevent executio ...

Y T

SEPS-6515 OPA-1102: It shall be possible to command the equipment/subs ...

Y T

SEPS-6516 OPA-81: Autonomy shall be divided into two separate functi ...

Y R

SEPS-6517 OPA-84: FDIR shall not trigger on one sample of a paramete ...

Y R


of 120




SEPS-6518 OPA-85: FDIR limits shall be set as wide as possible with ...

Y R

SEPS-6519 OPA-86: The FDIR functions implemented onboard should be i ...

Y R

SEPS-6520 OPA-87: For clearly identified critical mission phases fai ...

Y T,R

SEPS-6521 OPA-88: Hot redundancy shall be provided for functions whi ...

Y R

SEPS-6903 OPA-90: Spacecraft Autonomy shall be limited to the minimu ...

Y R

SEPS-6522 OPA-91: The Autonomy shall be implemented using determinis ...

Y R

SEPS-6527 OPA-96: All parameters used for autonomous operations (e.g ...

Y T

SEPS-6530 OPA-2128: For non-PUS based equipment the subcontractor shal ...

Y R

SEPS-6532 OPA-100: The spacecraft shall provide mechanisms to avoid o ...

Y T,A

SEPS-6534 OPA-102: Control of the autonomy shall be by high-level com ...

Y R

SEPS-6536 OPA-82: There shall be two separate levels of FDIR: Redund ...

Y T,R

SEPS-6537 OPA-83: The two levels of FDIR shall not interfere with ea ...

Y T,R

SEPS-6542 OPA-106: Whenever reasonably possible, the redundancy FDIR ...

Y R

SEPS-6543 OPA-107: Any potential conflict between failure recovery ac ...

Y T,R

SEPS-6544 OPA-109: For failures whose resolution does not imply safeg ...

Y T,R

SEPS-6545 OPA-110: The management of anomalies within a unit, subsyst ...

Y T,R

SEPS-6548 OPA-113: The fault management functions at all levels shall ...

Y T

SEPS-6904 OPA-114: The FDIR functions shall not be based on processin ...

Y R

SEPS-6549 OPA-116: The spacecraft shall manage the isolation of faile ...

Y T

SEPS-6550 OPA-117: For failures whose resolution implies safeguarding ...

Y T

SEPS-6551 OPA-118: A failure in the performance of an autonomous reco ...

Y T

SEPS-6552 OPA-119: The responses of the redundancy level FDIR to the ...

Y T

SEPS-6553 OPA-121: Failures that cannot be handled at a given level s ...

Y R

SEPS-6554 OPA-122: Where possible, failure recovery actions shall fir ...

Y R

SEPS-6555 OPA-123: If an onboard processor is switched from a main to ...

Y T

SEPS-6556 OPA-124: The activation of a redundant unit or functional p ...

Y R

SEPS-6557 OPA-126: Anomalies and actions taken to recover from them s ...

Y T


of 120




SEPS-6558 OPA-127: It shall be possible to reconstruct from telemetry ...

Y R

SEPS-6559 OPA-128: The fault management functions at all levels shall ...

Y T

SEPS-6560 OPA-129: Failure detection algorithms shall avoid continuou ...

Y T

SEPS-6561 OPA-130: Failure detection algorithms shall start generatio ...

Y T

SEPS-6562 OPA-131: It shall be possible for the Ground to enable/disa ...

Y T

SEPS-6563 OPA-132: For control of all FDIR Surveillances (i.e. low-le ...

Y T

SEPS-6564 OPA-133: It shall be possible to request a report of all de ...

Y T

SEPS-6565 OPA-134: The following FDIR surveillance information shall ...

Y T

SEPS-6905 OPA-154: The number of different Safe or Survival Modes sha ...

Y R

SEPS-6906 OPA-159: No nominal operation (including critical mission e ...

Y R

SEPS-6907 OPA-138: All onboard reconfigurations shall end with an una ...

Y T

SEPS-6908 OPA-139: The maximum duration of an onboard reconfiguration ...

Y T

SEPS-6909 OPA-140: Telemetry shall be available for the Ground to mon ...

Y T

SEPS-6910 OPA-141: The reconfiguration of onboard units or the switch ...

Y T,R

SEPS-6911 OPA-142: Telemetry indicating the cause of an onboard recon ...

Y T

SEPS-6912 OPA-143: The capability shall be provided to pre-configure ...

Y T

SEPS-6913 OPA-146: At power-up, restart and upon recovery from any po ...

Y T

SEPS-6914 OPA-147: The capability shall be provided for the Ground to ...

Y T,R

SEPS-6915 OPA-148: All defined combinations of main and redundant equ ...

Y T

SEPS-6916 OPA-149: Any selection of main or redundant equipment shall ...

Y T

SEPS-6917 OPA-150: Redundancy switching at unit level shall not requi ...

Y R

SEPS-6918 OPA-151: The onboard fault management shall avoid continuou ...

Y T,R

SEPS-6919 OPA-184: Telecommands shall be available to command all onb ...

Y T

SEPS-6566 OPA-185: No single command function executed at the wrong t ...

Y A

SEPS-6567 OPA-1409: The equipment/subsystem sub-contractor shall ident ...

Y A

SEPS-6568 OPA-1410: All hazardous commands shall be approved by ASD an ...

Y A

SEPS-6569 OPA-1412: Execution of equipment/subsystem hazardous functio ...

Y T


of 120




SEPS-6570 OPA-1413: The equipment/subsystem shall provide an unambiguo ...

Y T

SEPS-6571 OPA-186: Execution of identified vital functions (agreed by ...

Y T,R

SEPS-6573 OPA-188: It shall be possible to command all onboard device ...

Y T

SEPS-6574 OPA-1114: All switchable elements (e.g. relays or units with ...

Y R

SEPS-6920 OPA-190: The onboard reception, processing and execution of ...

Y T

SEPS-6575 OPA-191: Changes to onboard data or software parameters sha ...

Y R

SEPS-6576 OPA-192: Readouts of loaded onboard data or software parame ...

Y T

SEPS-6579 OPA-1117: It shall be possible to abort long duration teleco ...

Y T

SEPS-6580 OPA-1120: The equipment/subsystem shall provide the capabili ...

Y T

SEPS-6582 OPA-1122: The equipment or subsystem shall accept commands a ...

Y T

SEPS-6583 OPA-198: The Ground shall be provided on request throughout ...

Y T,R

SEPS-6584 OPA-199: The availability of telemetry information shall be ...

Y R

SEPS-6585 OPA-200: Telemetry data shall be provided on request to the ...

Y T,R

SEPS-6586 OPA-1125: The equipment or subsystem shall provide telemetry ...

Y T,R

SEPS-6587 OPA-202: Telemetry shall always be provided to unambiguousl ...

Y R

SEPS-6588 OPA-1132: The equipment/subsystem shall provide its status i ...

Y R

SEPS-6921 OPA-204: All mission critical functions shall be observable ...

Y T,R

SEPS-6589 OPA-1133: All inputs from equipment or subsystems to onboard ...

Y T,R

SEPS-6590 OPA-1134: Information to indicate all actions of operational ...

Y T,R

SEPS-6591 OPA-1135: The equipment/subsystem S/W status telemetry shall ...

Y R

SEPS-6592 OPA-208: The values of telemetry parameters shall be self-c ...

Y R

SEPS-6922 OPA-209: The value of a telemetry parameter shall be transm ...

Y R

SEPS-6593 OPA-1128: For trouble shooting purposes and failure analysis ...

Y T,R

SEPS-6923 OPA-1129: Parameter super-commutation is allowed in periodic ...

Y R

SEPS-6924 OPA-1130: A telemetry parameter shall always have the same s ...

Y R

SEPS-6594 OPA-1131: All spare fields within a telemetry data stream sh ...

Y R

SEPS-6925 OPA-1137: The handling of onboard telemetry shall be hierarc ...

Y R


of 120




SEPS-6595 OPA-214: Vital spacecraft health functions (e.g. primary bu ...

Y R

SEPS-6596 OPA-1138: Vital subsystem/equipment health functions (e.g. p ...

Y T

SEPS-6597 OPA-215: Telemetry shall be provided to enable detection an ...

Y R

SEPS-6598 OPA-216: Where telemetry measurements are processed onboard ...

Y T

SEPS-6599 OPA-217: For elements in hot redundancy, telemetry shall be ...

Y T

SEPS-6600 OPA-218: For elements in redundancy, the loss or failure of ...

Y T

SEPS-6601 OPA-1141: If the equipment/subsystem controls the redundancy ...

Y T

SEPS-6602 OPA-219: Telemetry parameters shall be sampled at a frequen ...

Y R

SEPS-6603 OPA-220: Sampling frequencies and sequences shall be define ...

Y R

SEPS-6604 OPA-221: Oversampling of telemetry parameters shall be poss ...

Y T

5.2.4.6 In-Flight Testing SEPS-6611 OPA-1253:

It shall be possible to activate any provided diag ... Y T

SEPS-6612 OPA-1254: No fault management function shall trigger on test ...

Y T,A

SEPS-6613 OPA-1255: Entering a test mode shall not require (or imply) ...

Y T,A

SEPS-6614 OPA-1256: Redundant units should provide the capability to b ...

Y T

SEPS-6615 OPA-1257: The capability shall be provided to load and check ...

Y T

SEPS-6926 OPA-1752: Each equipment/subsystem subcontractor shall defin ...

Y A

SEPS-6709 OPA-1779: An "are you alive" function shall be provided for ...

Y T

SEPS-6710 OPA-1782: All intelligent users shall be able to process a d ...

Y T

SEPS-6711 OPA-2150: The subcontractor shall propose and define his req ...

Y R

SEPS-6927 OPA-1785: Each equipment/subsystem subcontractor shall defin ...

Y A

SEPS-6712 OPA-1805: The subcontractor shall define which information h ...

Y R

SEPS-6721 OPA-2132: The subsystem/equipment User Manual (UM) shall add ...

Y R

SEPS-6722 OPA-2133: The subsystem/equipment UM shall provide the custo ...

Y R

SEPS-6723 OPA-2134: The content of the UM shall include: · A complete ...

Y R

SEPS-6724 OPA-2135: All subsystem/equipment procedures in the UM shall ...

Y T

SEPS-6725 OPA-2136: The contents of the UM shall be internally consist ...

Y R


of 120




SEPS-6726 OPA-2137: The content of the UM shall be consistent with the ...

Y R

SEPS-6727 OPA-2138: The content of the UM shall be consistent with the ...

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SEPS-6728 OPA-2142: The database shall contain: · the complete defini ...

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SEPS-6729 OPA-2143: The contents of the database shall be internally c ...

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SEPS-6730 OPA-2144: TM and TC parameters shall contain a description o ...

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SEPS-6731 OPA-2145: In addition to this database a TM/TC ICD shall be ...

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Requirement/Section Cross Reference Page numbers are the pages where the sections start

SEPS-10............. 2.1....................9 SEPS-16............. 3.2.1.................11 SEPS-18............. 3.2.2.................11 SEPS-19............. 3.2.2.................11 SEPS-20............. 3.2.2.................11 SEPS-21............. 3.2.2.................11 SEPS-22............. 3.2.4.................12 SEPS-23............. 3.2.4.................12 SEPS-24............. 3.2.3.................11 SEPS-26............. 3.2.5.................12 SEPS-27............. 3.2.5.................12 SEPS-28............. 3.2.5.................12 SEPS-29............. 3.2.5.................12 SEPS-30............. 3.2.5.................12 SEPS-31............. 3.2.5.................12 SEPS-32............. 3.2.5.................12 SEPS-33............. 3.2.5.................12 SEPS-35............. 3.2.6.................13 SEPS-36............. 3.2.6.................13 SEPS-37............. 3.2.6.................13 SEPS-39............. 3.2.7.3..............15 SEPS-40............. 3.2.7.3..............15 SEPS-41............. 3.2.7.4..............16 SEPS-43............. 3.2.7.3..............15 SEPS-44............. 3.2.7.5..............16 SEPS-45............. 3.2.7.5..............16 SEPS-46............. 3.2.7.3..............15 SEPS-48............. 3.2.7.6..............17 SEPS-51............. 3.3.10.3............24 SEPS-52............. 3.3.10.3............24 SEPS-55............. 3.3.1.................19 SEPS-56............. 3.3.1.................19 SEPS-57............. 3.3.1.................19 SEPS-58............. 3.3.6.................21 SEPS-59............. 3.3.6.................21 SEPS-60............. 3.3.6.................21 SEPS-61............. 3.3.2.................19 SEPS-62............. 3.3.3.................20 SEPS-63............. 3.3.4.................20 SEPS-64............. 3.3.5.................21 SEPS-65............. 3.3.5.................21 SEPS-66............. 3.3.9.................22 SEPS-67............. 3.3.10.1............22 SEPS-68............. 3.3.10.1............22 SEPS-69............. 3.3.10.1............22 SEPS-70............. 6.2.3.1..............48 SEPS-71............. 6.2.3.1..............48 SEPS-72............. 6.2.3.1..............48 SEPS-73............. 3.3.10.1............22 SEPS-78............. 3.3.8.2..............22 SEPS-80............. 4.3.4.1..............39 SEPS-81............. 4.3.4.1..............39 SEPS-82............. 4.3.4.1..............39 SEPS-84............. 4.3.4.3..............39 SEPS-85............. 4.3.4.3..............39 SEPS-86............. 4.3.4.3..............39 SEPS-87............. 4.3.4.3..............39

SEPS-88 .............4.3.4.3 ............. 39 SEPS-89 .............4.3.4.3 ............. 39 SEPS-100 ...........3.3.10.2 ........... 24 SEPS-101 ...........3.3.10.2 ........... 24 SEPS-118 ...........4.4.1 ................ 40 SEPS-124 ...........4.4.2 ................ 41 SEPS-132 ...........4.3.3 ................ 38 SEPS-133 ...........4.3.3 ................ 38 SEPS-149 ...........4.1.2.1.2 .......... 26 SEPS-150 ...........4.1.2.1.2 .......... 26 SEPS-151 ...........4.1.2.1.2 .......... 26 SEPS-154 ...........3.3.8.1 ............. 21 SEPS-155 ...........3.3.8.1 ............. 21 SEPS-160 ...........4.3.2.1 ............. 38 SEPS-161 ...........4.3.2.1 ............. 38 SEPS-163 ...........4.3.2.2 ............. 38 SEPS-164 ...........4.3.2.2 ............. 38 SEPS-167 ...........4.3.1 ................ 38 SEPS-175 ...........4.1.3.1 ............. 27 SEPS-177 ...........4.1.3.1 ............. 27 SEPS-178 ...........4.1.3.1 ............. 27 SEPS-179 ...........4.1.3.1.1 .......... 27 SEPS-180 ...........4.1.3.1.3 .......... 28 SEPS-181 ...........4.1.3.1.3 .......... 28 SEPS-182 ...........4.1.3.1.3 .......... 28 SEPS-185 ...........4.1.3.2 ............. 29 SEPS-187 ...........4.1.3.2 ............. 29 SEPS-198 ...........4.1.4.1 ............. 30 SEPS-200 ...........4.1.4.1 ............. 30 SEPS-201 ...........4.1.4.1 ............. 30 SEPS-202 ...........6.2.3.1 ............. 48 SEPS-203 ...........4.1.4.1 ............. 30 SEPS-205 ...........4.1.4.2 ............. 30 SEPS-211 ...........4.1.4.3.1 .......... 31 SEPS-213 ...........4.1.4.3.1 .......... 31 SEPS-215 ...........4.1.4.3 ............. 30 SEPS-217 ...........4.1.4.3 ............. 30 SEPS-219 ...........4.1.4.3 ............. 30 SEPS-260 ...........4.1.4.4.3 .......... 32 SEPS-281 ...........4.2.2.2 ............. 36 SEPS-325 ...........5 ...................... 42 SEPS-344 ...........3.2.1 ................ 11 SEPS-353 ...........3.2.7.3 ............. 15 SEPS-354 ...........3.2.7.3 ............. 15 SEPS-355 ...........3.2.7.3 ............. 15 SEPS-356 ...........3.2.7.4 ............. 16 SEPS-357 ...........3.2.7.4 ............. 16 SEPS-362 ...........3.3 ................... 18 SEPS-363 ...........3.3 ................... 18 SEPS-367 ...........3.3.4 ................ 20 SEPS-368 ...........3.3.2 ................ 19 SEPS-369 ...........3.3.4 ................ 20 SEPS-370 ...........3.3.4 ................ 20 SEPS-376 ...........3.3.10.1 ........... 22 SEPS-385 ...........3.3.10.1 ........... 22 SEPS-386 ...........3.3.10.1 ........... 22 SEPS-390 ...........4.1.1.2 ............. 26

SEPS-392........... 4.1.1.3 ..............26 SEPS-401........... 3.2.7.6 ..............17 SEPS-402........... 4.2 ....................35 SEPS-403........... 4.2.1 .................35 SEPS-405........... 4.2.1 .................35 SEPS-406........... 4.2.1 .................35 SEPS-407........... 4.2.1 .................35 SEPS-408........... 4.2.1 .................35 SEPS-409........... 4.2.1 .................35 SEPS-410........... 4.2.1 .................35 SEPS-411........... 4.2.1 .................35 SEPS-412........... 4.2.1 .................35 SEPS-414........... 4.2.1 .................35 SEPS-415........... 4.2.1 .................35 SEPS-416........... 4.2.1 .................35 SEPS-418........... 4.2.2 .................36 SEPS-425........... 4.2.2.2 ..............36 SEPS-429........... 4.2.2.2 ..............36 SEPS-434........... 4.2.2.2 ..............36 SEPS-476........... 6.1.1 .................44 SEPS-478........... 6.1.2 .................44 SEPS-480........... 6.1.3 .................44 SEPS-481........... 6.1.3 .................44 SEPS-482........... 6.1.3 .................44 SEPS-484........... 6.1.4 .................44 SEPS-486........... 6.1.5 .................44 SEPS-488........... 6.2 ....................46 SEPS-489........... 6.2 ....................46 SEPS-494........... 6.2.1.1 ..............46 SEPS-496........... 6.2.1.2 ..............46 SEPS-497........... 6.2.1.2 ..............46 SEPS-498........... 6.2.1.2 ..............46 SEPS-499........... 6.2.1.2 ..............46 SEPS-502........... 6.2.2.1 ..............46 SEPS-503........... 6.2.2.1 ..............46 SEPS-505........... 6.2.2.2 ..............47 SEPS-552........... 6.2.2.3 ..............48 SEPS-556........... 6.2.2.4 ..............48 SEPS-558........... 6.2.2.5 ..............48 SEPS-561........... 6.2.3.2 ..............49 SEPS-562........... 6.2.3.2 ..............49 SEPS-564........... 6.2.3.2 ..............49 SEPS-565........... 6.2.3.2 ..............49 SEPS-566........... 6.2.3.2 ..............49 SEPS-568........... 6.2.3.3 ..............50 SEPS-569........... 6.2.3.3 ..............50 SEPS-654........... 6.2.3.4 ..............51 SEPS-656........... 6.2.3.5 ..............51 SEPS-658........... 6.2.3.6 ..............51 SEPS-661........... 6.3.1 .................51 SEPS-662........... 6.3.1 .................51 SEPS-663........... 6.3.1 .................51 SEPS-664........... 6.3.1 .................51 SEPS-666........... 6.3.2 .................52 SEPS-670........... 6.3.3 .................52 SEPS-672........... 6.3.4 .................53 SEPS-674........... 6.3.5 .................53


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SEPS-676........... 6.3.6.................53 SEPS-678........... 6.4....................53 SEPS-680........... 6.4.1.................53 SEPS-682........... 6.4.1.1..............53 SEPS-686........... 6.4.1.2..............53 SEPS-688........... 6.4.1.3..............54 SEPS-690........... 6.4.1.4..............54 SEPS-692........... 6.4.2.................54 SEPS-693........... 6.4.2.................54 SEPS-694........... 6.4.2.................54 SEPS-695........... 6.4.2.................54 SEPS-698........... 6.4.7.1..............57 SEPS-699........... 6.4.7.1..............57 SEPS-700........... 6.4.7.1..............57 SEPS-701........... 6.4.7.1..............57 SEPS-702........... 6.4.7.1..............57 SEPS-703........... 6.4.7.1..............57 SEPS-704........... 6.4.7.1..............57 SEPS-705........... 6.4.7.1..............57 SEPS-707........... 6.4.7.1..............57 SEPS-708........... 6.4.7.1..............57 SEPS-710........... 6.4.7.1..............57 SEPS-711........... 6.4.7.1..............57 SEPS-713........... 6.4.7.1..............57 SEPS-715........... 6.4.7.2..............58 SEPS-716........... 6.4.7.2..............58 SEPS-717........... 6.4.7.2..............58 SEPS-718........... 6.4.7.2..............58 SEPS-720........... 6.4.7.3..............59 SEPS-721........... 6.4.7.3..............59 SEPS-722........... 6.4.7.3..............59 SEPS-723........... 6.4.7.3..............59 SEPS-725........... 6.4.3.................55 SEPS-726........... 6.4.3.................55 SEPS-736........... 6.4.11.1............60 SEPS-737........... 6.4.11.1............60 SEPS-738........... 6.4.11.1............60 SEPS-739........... 6.4.11.1............60 SEPS-740........... 6.4.11.1............60 SEPS-741........... 6.4.11.1............60 SEPS-742........... 6.4.11.1............60 SEPS-743........... 6.4.11.1............60 SEPS-744........... 6.4.11.1............60 SEPS-747........... 6.4.11.2............61 SEPS-748........... 6.4.11.2............61 SEPS-749........... 6.4.11.2............61 SEPS-750........... 6.4.11.2............61 SEPS-752........... 6.4.4.................55 SEPS-753........... 6.4.4.................55 SEPS-754........... 6.4.4.................55 SEPS-755........... 6.4.4.................55 SEPS-756........... 6.4.4.................55 SEPS-757........... 6.4.4.................55 SEPS-758........... 6.4.4.................55 SEPS-759........... 6.4.4.................55 SEPS-761........... 6.4.8.................59 SEPS-762........... 6.4.8.................59 SEPS-763........... 6.4.8.................59 SEPS-764........... 6.4.8.................59 SEPS-765........... 6.4.8.................59

SEPS-766 ...........6.4.8 ................ 59 SEPS-768 ...........6.4.8 ................ 59 SEPS-772 ...........6.4.9 ................ 59 SEPS-773 ...........6.4.9 ................ 59 SEPS-775 ...........6.4.9 ................ 59 SEPS-831 ...........6.4.12 .............. 61 SEPS-833 ...........6.4.13 .............. 61 SEPS-837 ...........6.4.14 .............. 61 SEPS-838 ...........6.4.14 .............. 61 SEPS-840 ...........6.4.14 .............. 61 SEPS-842 ...........6.5 ................... 62 SEPS-846 ...........4.3.4.2 ............. 39 SEPS-847 ...........4.3.4.2 ............. 39 SEPS-848 ...........3.2.7.3 ............. 15 SEPS-849 ...........6.1.6 ................ 45 SEPS-850 ...........6.1.6 ................ 45 SEPS-851 ...........6.1.6 ................ 45 SEPS-852 ...........6.1.6 ................ 45 SEPS-856 ...........6.1 ................... 44 SEPS-857 ...........6.1.6 ................ 45 SEPS-858 ...........6.1.6 ................ 45 SEPS-859 ...........3.2.7.6 ............. 17 SEPS-860 ...........3.2.7.6 ............. 17 SEPS-861 ...........3.2.7.3 ............. 15 SEPS-863 ...........4.3.4.2 ............. 39 SEPS-864 ...........4.4.1 ................ 40 SEPS-865 ...........4.4.1 ................ 40 SEPS-866 ...........3.2.2 ................ 11 SEPS-868 ...........3.2.7.2 ............. 13 SEPS-869 ...........3.2.7.2 ............. 13 SEPS-870 ...........3.2.7.2 ............. 13 SEPS-871 ...........3.2.7.2 ............. 13 SEPS-872 ...........3.2.7.2 ............. 13 SEPS-873 ...........3.2.7.2 ............. 13 SEPS-874 ...........3.2.7.2 ............. 13 SEPS-875 ...........3.2.7.2 ............. 13 SEPS-876 ...........3.2.7.2 ............. 13 SEPS-877 ...........3.2.7.2 ............. 13 SEPS-878 ...........3.2.7.2 ............. 13 SEPS-881 ...........3.2.7.5 ............. 16 SEPS-883 ...........3.2.7.5 ............. 16 SEPS-884 ...........3.2.7.2 ............. 13 SEPS-885 ...........3.2.7.5 ............. 16 SEPS-888 ...........3.3.7 ................ 21 SEPS-889 ...........3.3.7 ................ 21 SEPS-890 ...........3.3.4 ................ 20 SEPS-891 ...........4.1.3.1 ............. 27 SEPS-894 ...........6.4.5 ................ 55 SEPS-896 ...........6.4.5.1 ............. 55 SEPS-898 ...........6.4.5.2 ............. 56 SEPS-900 ...........6.4.5.3 ............. 56 SEPS-903 ...........6.4.6.1 ............. 57 SEPS-905 ...........6.4.6.2 ............. 57 SEPS-906 ...........6.4.6.1 ............. 57 SEPS-908 ...........6.4.5.5 ............. 56 SEPS-910 ...........6.4.6.3 ............. 57 SEPS-911 ...........6.4.6.1 ............. 57 SEPS-914 ...........6.4.6.4 ............. 57 SEPS-915 ...........6.2.2.2 ............. 47 SEPS-916 ...........6.2.2.2 ............. 47

SEPS-917........... 6.4.9 .................59 SEPS-918........... 6.4.9 .................59 SEPS-919........... 6.4.9 .................59 SEPS-920........... 6.4.9 .................59 SEPS-921........... 6.4.9 .................59 SEPS-922........... 6.4.9 .................59 SEPS-924........... 6.2.3.3 ..............50 SEPS-925........... 6.4.10 ...............60 SEPS-926........... 6.4.10 ...............60 SEPS-927........... 6.4.10 ...............60 SEPS-928........... 3.3.10.1 ............22 SEPS-929........... 3.3.10.1 ............22 SEPS-930........... 6.2.3.1 ..............48 SEPS-937........... 4.1.5.1.1 ...........32 SEPS-942........... 4.1.5.1.2 ...........32 SEPS-944........... 4.1.5.1.3 ...........32 SEPS-946........... 4.1.5.1.4 ...........32 SEPS-950........... 4.1.5.1.5 ...........33 SEPS-952........... 4.1.5.1.6 ...........33 SEPS-953........... 4.1.5.1.6 ...........33 SEPS-956........... 4.1.5.1.7 ...........33 SEPS-957........... 4.1.5.1.7 ...........33 SEPS-958........... 4.1.5.1.7 ...........33 SEPS-960........... 4.1.5.1.7 ...........33 SEPS-961........... 4.1.5.1.7 ...........33 SEPS-962........... 4.1.5.1.7 ...........33 SEPS-963........... 4.1.5.1.7 ...........33 SEPS-964........... 4.1.5.1.7 ...........33 SEPS-965........... 4.1.5.1.7 ...........33 SEPS-966........... 4.1.5.1.7 ...........33 SEPS-967........... 4.1.5.1.7 ...........33 SEPS-969........... 4.1.5.1.8 ...........34 SEPS-970........... 4.1.5.1.8 ...........34 SEPS-971........... 4.1.5.1.8 ...........34 SEPS-972........... 4.1.5.1.8 ...........34 SEPS-976........... 4.1.5.1.9 ...........34 SEPS-977........... 4.1.5.1.9 ...........34 SEPS-978........... 4.1.5.1.9 ...........34 SEPS-979........... 4.1.5.1.9 ...........34 SEPS-981........... 4.1.5.1.10 .........34 SEPS-986........... 4.1.5.1.11 .........35 SEPS-988........... 3.2.7.3 ..............15 SEPS-989........... 3.2.7.3 ..............15 SEPS-990........... 6.1.6 .................45 SEPS-992........... 2.1 ....................9 SEPS-995........... 2.1 ....................9 SEPS-996........... 2.1 ....................9 SEPS-997........... 2.1 ....................9 SEPS-1001......... 2.1 ....................9 SEPS-1002......... 2.1 ....................9 SEPS-1003......... 2.1 ....................9 SEPS-1007......... 2.1 ....................9 SEPS-1008......... 2.1 ....................9 SEPS-1009......... 2.1 ....................9 SEPS-1013......... 2.1 ....................9 SEPS-1014......... 2.1 ....................9 SEPS-1015......... 2.1 ....................9 SEPS-1019......... 2.1 ....................9 SEPS-1020......... 2.1 ....................9 SEPS-1021......... 2.1 ....................9


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SEPS-1025......... 2.1....................9 SEPS-1026......... 2.1....................9 SEPS-1027......... 2.1....................9 SEPS-1031......... 2.1....................9 SEPS-1032......... 2.1....................9 SEPS-1033......... 2.1....................9 SEPS-1049......... 2.1....................9 SEPS-1050......... 2.1....................9 SEPS-1051......... 2.1....................9 SEPS-1103......... 2.1....................9 SEPS-1104......... 2.1....................9 SEPS-1105......... 2.1....................9 SEPS-1145......... 2.1....................9 SEPS-1146......... 2.1....................9 SEPS-1147......... 2.1....................9 SEPS-1151......... 2.1....................9 SEPS-1152......... 2.1....................9 SEPS-1153......... 2.1....................9 SEPS-2569......... 6.2.3.1..............48 SEPS-4823......... 6.2.3.1..............48 SEPS-4826......... 4.1.4.4.3...........32 SEPS-4828......... 4.1.4.4.3...........32 SEPS-4829......... 3.3.10.3............24 SEPS-4836......... 4.1.4.3.1...........31 SEPS-4837......... 4.1.4.3.1...........31 SEPS-4838......... 4.1.4.3.1...........31 SEPS-4839......... 4.1.4.3.1...........31 SEPS-4840......... 4.1.4.3.1...........31 SEPS-4841......... 4.1.4.3.1...........31 SEPS-4842......... 4.1.4.3.1...........31 SEPS-4843......... 4.1.4.3.1...........31 SEPS-4848......... 4.2.2.2..............36 SEPS-4913......... 3.2.6.................13 SEPS-4915......... 3.2.7.7..............18 SEPS-4916......... 3.3....................18 SEPS-4919......... 6.4.5.4..............56 SEPS-5245......... 3.2.7.5..............16 SEPS-5246......... 3.2.7.6..............17 SEPS-5247......... 3.2.7.6..............17 SEPS-5317......... 4.1.4.2..............30 SEPS-5326......... 6.4.4.................55 SEPS-5327......... 6.4.9.................59 SEPS-5330......... 4.3.4.2..............39 SEPS-5331......... 6.1.6.................45 SEPS-5332......... 6.1.6.................45 SEPS-5333......... 3.2.7.2..............13 SEPS-5334......... 3.2.7.6..............17 SEPS-5851......... 4.1.4.4.1...........31 SEPS-5852......... 4.1.4.4.2...........32 SEPS-5859......... 3.2.7.4..............16 SEPS-5861......... 3.2.7.4..............16 SEPS-5862......... 3.3.5.................21 SEPS-5946......... 4.1.3.1.2...........27 SEPS-5947......... 4.1.3.1.2...........27 SEPS-5948......... 4.1.3.1.2...........27 SEPS-5949......... 4.1.3.1.2...........27 SEPS-5951......... 4.1.3.1.1...........27 SEPS-5952......... 4.1.3.1..............27 SEPS-5955......... 4.1.3.1.3...........28 SEPS-5970......... 5.1....................42

SEPS-5971 .........5.1 ................... 42 SEPS-5973 .........5.1 ................... 42 SEPS-5976 .........4.1.4.4.3 .......... 32 SEPS-5977 .........4.1.3.2 ............. 29 SEPS-5978 .........4.1.3.2 ............. 29 SEPS-5980 .........4.1.3.2 ............. 29 SEPS-5981 .........4.1.3.2 ............. 29 SEPS-5990 .........4.2.2.1.1 .......... 36 SEPS-5991 .........4.2.2.1.2 .......... 36 SEPS-5997 .........4.1.4.5 ............. 32 SEPS-6001 .........3.3.8.2 ............. 22 SEPS-6002 .........4.1.3.1.3 .......... 28 SEPS-6003 .........3.2.7.3 ............. 15 SEPS-6057 .........3.2.7.7 ............. 18 SEPS-6058 .........3.2.7.7 ............. 18 SEPS-6064 .........4.1.4.3.1 .......... 31 SEPS-6114 .........4.2.3.1 ............. 37 SEPS-6115 .........4.2.3.1 ............. 37 SEPS-6116 .........4.2.3.1 ............. 37 SEPS-6136 .........3.2.7.7 ............. 18 SEPS-6138 .........4.1.3.2 ............. 29 SEPS-6142 .........4.1.2.1.1 .......... 26 SEPS-6143 .........4.1.2.1.1 .......... 26 SEPS-6744 .........4.1.3.1 ............. 27 SEPS-6745 .........4.1.3.1 ............. 27 SEPS-6747 .........4.2.3.1 ............. 37


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