sog srs pl 00300 a sar intrument v&v plan

SOG-SRS-PL-00300-A

08-Sep-2011

PLAN

SAR INSTRUMENT VERIFICATION & VALIDATION PLAN

SAOCOM PROJECT COMISION NACIONAL DE ACTIVIDADES ESPACIALES

BUENOS AIRES – ARGENTINA

COMISION NACIONAL DEACTIVIDADES ESPACIALES

SAOCOM PROJECT

DOC: SOG-SRS-PL-00300-A

PAGES: 40

DATE: 08-Sep-2011

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Annex A

5

Distribution List

Name Company Copy Name Company Copy

Amarfil, M. Barrientos, C.

Benito, G. Bratina, J.

Castello, N. Cuesta Gonzalez, J.

Defelippe, C. Garategaray, L.

Gonzalez, G. Hofmann, C.

Kulichevsky, R. Marín, J.

Marino, P.

CONAE STI

INVAP CONAE CONAE CONAE CONAE CONAE CONAE CONAE CONAE CONAE CONAE

1 2 3 4 5 6 7 8 9 10 11 12 13

Martin Ghiselli, A. Mascialino, H.

Medina, J. Ordoñez, P.

Peres, J. Petruccioli, M. Ringegni, P. Rodolico, M. Roggero, E.

Siman, J. Skora, J. Vega, J.

CNEA CONAE CONAE CONAE CONAE CONAE GEMA

CONAE CONAE

DTA CONAE CONAE

14 15 16 17 18 19 20 21 22 23 24 25

DOCUMENT CHANGE RECORD

ISSUE DATE CHANGE NOTICE CHANGE DESCRIPTION

Comisión Nacional de Actividades Espaciales (CONAE) from Argentina 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 be only reproduced, copied or communicated, in whole or in part, for internal use of CONAE, directly or by third parties holding confidentiality agreements with CONAE. Any person other than the authorised holder obtaining possession of this document by finding or otherwise, should send it, together with his name and address, in a sealed envelope to: Comisión Nacional de Actividades Espaciales (CONAE) – SAOCOM Project Av. Paseo Colón 751 (C1063ACH) Capital Federal ARGENTINA

Letter postage need not be prepaid. Other postage will be refunded.

DOC: SOG-SRS-PL-00300-A SAR INSTRUMENT VERIFICATION & VALIDATION PLAN 08-Sep-11

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INDEX

PAGE ISSUE LETTER RECORD ....................................................................................................................................2

DOCUMENT CHANGE RECORD...................................................................................................................................3

1. OBJECTIVE ................................................................................................................................................................6

2. SCOPE ..........................................................................................................................................................................6

3. APPLICABILITY .......................................................................................................................................................6

4. APPLICABLE DOCUMENTS ..................................................................................................................................6

5. REFERENCE DOCUMENTS ...................................................................................................................................6

6. ACRONYMS AND ABBREVIATIONS...................................................................................................................7

7. DEFINITIONS.............................................................................................................................................................9

8. SAR INSTRUMENT DESCRIPTION......................................................................................................................9

9. V&V APPROACH ....................................................................................................................................................13

10. VERIFICATION & VALIDATION PROCESS ...............................................................................................14

10.1. VERIFICATION PLAN APPROACH...............................................................................................................14

10.2. VERIFICATION IMPLEMENTATION...........................................................................................................14

10.3. SAR INSTRUMENT L3 REQUIREMENTS VALIDATION PROCESS .....................................................16

10.4. SAR INSTRUMENT L3 REQUIREMENTS VERIFICATION PROCESS .................................................16

11. VERIFICATION METHODS.............................................................................................................................17

11.1. TEST.......................................................................................................................................................................17

11.2. ANALYSIS.............................................................................................................................................................17

11.3. SIMILARITY ........................................................................................................................................................17

11.4. INSPECTION........................................................................................................................................................17

11.5. DEMONSTRATION ............................................................................................................................................18

11.6. VALIDATION OF RECORDS ...........................................................................................................................18

12. VERIFICATION PHASES..................................................................................................................................18

12.1. DEVELOPMENT .................................................................................................................................................18

12.2. QUALIFICATION................................................................................................................................................18

12.3. ACCEPTANCE .....................................................................................................................................................19

12.4. PRE-LAUNCH ......................................................................................................................................................19

12.5. FLIGHT / MISSION.............................................................................................................................................19

13. V&V RESPONSIBILITIES.................................................................................................................................19

13.1. CONAE´S RESPONSIBILITIES........................................................................................................................19

13.2. PROVIDING ORGANIZATIONS RESPONSIBILITIES ..............................................................................20

14. V&V DOCUMENTATION..................................................................................................................................21

14.1. REQUIREMENT VERIFICATION AND VALIDATION MATRIX ...........................................................21

14.2. VERIFICATION PROCESS AND THE RELATED DOCUMENTATION ................................................22

14.2.1. ENVIRONMENTAL TEST AUTHORIZATION AND SUMMARY (ETAS) .........................................23

14.2.2. TEST SPECIFICATION .................................................................................................................................23

14.2.3. TEST PROCEDURE........................................................................................................................................23

14.2.4. TEST REPORT ................................................................................................................................................23

14.2.5. ANALYSIS REPORT ......................................................................................................................................23


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14.2.6. INSPECTION REPORT..................................................................................................................................23

14.2.7. VERIFICATION REPORT ............................................................................................................................23

14.2.8. OTHER DOCUMENTS...................................................................................................................................23

15. SAR INTRUMENT V&V STRATEGY .............................................................................................................24

16. QUALIFICATION AND FLIGHT MODELS ..................................................................................................24

16.1. QUALIFICATION MODELS.............................................................................................................................24

16.1.1. SAR ANTENNA STRUCTURAL MODEL ..................................................................................................25

16.1.2. SAR ANTENNA PANEL THERMAL QUALIFICATION MODEL........................................................25

16.1.3. SAR ANTENNA PANEL ENGINEERING MODEL..................................................................................26

16.1.3.1. VERIFICATION FLOW ..........................................................................................................................26

16.1.4. RADIOMETRIC ANTENNA MATHEMATICAL MODEL.....................................................................26

16.1.5. SAR ANTENNA STRUCTURAL MATHEMATICAL MODEL ..............................................................27

16.1.6. SAR ANTENNA THERMAL MATHEMATICAL MODEL .....................................................................27

16.1.7. SAR CENTRAL ELECTRONICS ENGINEERING MODEL ..................................................................27

16.1.8. SAR DDL ENGINEER MODEL....................................................................................................................27

16.1.9. SAR INSTRUMENT ENGINEERING MODEL (EM) ...............................................................................27

SAR ANTENNA EMULATOR (EMANTSAR)..............................................................................................................28

16.1.9.1. VERIFICATION FLOW ..........................................................................................................................28

16.2. PROTO-FLIGHT & FLIGHT MODELS..........................................................................................................29

16.2.1. VERIFICATION FLOW.................................................................................................................................30

16.2.2. PROTO-FLIGHT MODEL.............................................................................................................................30

16.2.3. FLIGHT MODEL.............................................................................................................................................30

17. VERIFICATION MATRIX FOR SAR INSTRUMENT MODELS...............................................................31

18. TEST FACILITIES ..............................................................................................................................................35

18.1. ENVIRONMENTAL TEST FACILITIES ........................................................................................................35

18.2. INTEGRATION, ASSEMBLY, AND TEST .....................................................................................................35

18.3. OTHER ARGENTINE FACILITIES ................................................................................................................35

ANNEX A: COMPLETE V&V MATRIX ......................................................................................................................36


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1. OBJECTIVE This document establishes the requirements for the Verification & Validation (V&V) processes

and activities to be implemented to warrant the adequate performance of the SAR Instrument in the required environmental conditions for the mission.

2. SCOPE This Plan defines the overall V&V philosophy at the SAR Instrument and SAR Antenna Module

levels

3. APPLICABILITY This document contains the overall verification approach, the verification strategies for the SAR

Instrument, the test program, the involved documentation, the verification management and organization. Its principal use is to provide a according V&V program and its proposed elements.

4. APPLICABLE DOCUMENTS [AD1] SOG-SYG-RQ-00200, “MISSION SYSTEM REQUIREMENTS” [AD2] SOG-ENV-RQ-00100, “ENVIRONMENTAL REQUIREMENT DOCUMENT” [AD3] SOG-SMA-PL-00300 “SYSTEM SAFETY PLAN” [AD4] SOG-VYV-SP-00100 “PROCEDURAL ENVIRONMENTAL VERIFICATION REQUIREMENTS” [AD5] SOG-VYV-PL-00100 “SAOCOM PROJECT VERIFICATION & VALIDATION PLAN” [AD6] SOR-SRS-RQ-00100 L3 SAR Requirements [AD7] SOG-SMA-RQ-00100 L2B Safety and Product Assurance Requirements Document [AD8] SOR-SRS-DS-00300 SAR Instrument Design Description

5. REFERENCE DOCUMENTS [RD1] NASA GSFC-STD-7000, “GENERAL ENVIRONMENTAL VERIFICATION STANDARD (GEVS)” [RD2] ESA ECSS-E-10-02A “VERIFICATION” [RD3] 0804-RSTI-GEDCS-002, SAR CE FUNCTIONAL DESCRIPTION [RD4] SOR-NTE-NT-00100, Antena SAR: Configuración y Descripción de sus Componentes SAR Instrument [RD5] 0804-RIOG-GUBCF-001-A SAR Instrument Interface Control Document Through the S-Band Channel [RD6] 0804-RIOG-GUBCF-002-A SAR Instrument Interface Control Document Through the X-Band Channel [RD7] GS-CGS-CPR-SP-00200-B CONAE Telecommand Format Specification [RD8] GS-CGS-CPR-SP-00300-B CONAE Telemetry Format Specification [RD9] 0804-PGGG-GZDCS-006-A SAOCOM Telemetry Data Reference [RD10] SOR-SRS-NT-00100-A INSTRUMENTO SAR, DESCRIPCION FUNCIONAL SAR CE [RD11] 0804-RSTI-GEDCS-002 SAR CE, Functional Description [RD12] 804-RSFI-GEBCS-002-B SAR CE, EM ICD. [RD13] 0804-RSFI-GEACS-001-A SAR CE, EM Electrical Configuration. [RD14] 0804-RPRG-YBBCJ-002-A SAR CE, POWER, Subsystem Design [RD15] 0804-RZSG-YBBCJ-002-B SAR CE, SSG, Subsystem Design [RD16] 0804-RZRG-YBBCJ-002-C SAR CE, CRX, Subsystem Design [RD17] 0804-RZAG-YBBCJ-002-C SAR CE, TRRS, Subsystem Design [RD18] 0804-RZTG-YBBCJ-002-A SAR CE, CTX, Subsystem Design [RD19] 0804-RCCG-YBBCJ-002-A SAR CE, CDU, Subsystem Design [RD20] 0804-RCSG-YBBCJ-002-A SAR CE, SSR, Subsystem Design [RD21] 0804-RCWG-YBBCF-001-B SAR CE, CDU, SW Architecture Design [RD22] 0804-RCWG-YBBCF-002-A SAR CE, SSR, SW Architecture Design [RD23] 0804-RSII-GEFCS-001 SAR CE, INTEGRATION & TEST PLAN (EM STAGE)


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SAR DDL [RD24] 0804-RDYI-GEBCJ-001-A SAOCOM, SAR DDL, Configuración Eléctrica EM SAR Antenna [RD25] SOR-CTR-RQ-00100: CTR Technical Requirements - CONAE [RD26] SOR-NTR-RQ-00100-E: TRM Technical Requirements - CONAE [RD27] SOR-NTR-RQ-00300-E:Technical Requirement Specification for Power Supply Unit-CONAE [RD28] SOR-CDA-RQ-00100-C: Requerimientos para el Harness de la Antena SAR - CONAE [RD29] SOR-CDA-DS-00100-D: Diseño conceptual del cableado de la antena SAR - CONAE [RD30] SOR-CDA-IC-00100-A: Interfaz EC con la Antena del SAR-SAOCOM - CONAE [RD31] SOR-CDA-NT-00100-B: Dimensionamiento de los cables y conectores de la ant. SAR-CONAE [RD32] SOR-RDE-RQ-00100: SL&DA: Requerimientos de la Unidad de Control - CONAE [RD33] SOR-RDE-PL-00300-B: SL&DA: Plan de ensayos de la electrónica de despliegue - CONAE [RD34] SOR-RDE-RP-00100-A: SL&DA: Arquitectura y Configuración - CONAE [RD35] SOR-RDE-DG-00100-A: Descripción de la electrónica de las Unidades de Control -CONAE

6. ACRONYMS AND ABBREVIATIONS A/T: Analisys & Test Acp: Acceptance Level ARB: Antena Relay Box. Assy:Assembly CDH: Command and Data Handling. CDPU: Control and Data Processing Unit. CDU: Control and Digitization Unit. CNEA: Comisión Nacional de Energía Atómica COC: Certificated of Compliance. CoG: Centre of Gravity CoNAE: Comisión Nacional de Actividades Espaciales CRX: Central Receiver. CTR: Conjunto de Transmisión/Recepción (in the SAR ANtenna). CTX: Central Transmitter. DDL: Data Downlink System. DP: Development Panel EIDP: End Item Data Package. EM: Engineering Model EPC: Electrical Power Conditioner (equipo del DDL). EQM: Engineering Qualification Model ERD: Environmental Requirement Document FEM: Finite Element Model g: Gravity Acceleration GS: Ground Segment GSE: Ground Support Equipment HLSS: High Level Sine Sweep HW: Hardware LLSS Low Level Sine Sweep MGSE Mechanical Ground Support Equipment MOD: Modulador de Banda X (equipo del DDL). MTR: Módulo Tx-Rx. NEC: Núcleo de la Electrónica Central del SAR. P/FR Problem/ Failure Report PFM: Proto-Flight Model PFM:Proto-Flight Model Q: Qualification QA: Quality Assurance.


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QM: Qualification Model RDVM: Radiation Diagram Verification Model RFDN: RF Distribution Network. RTUCE: Remote Terminal Unit Central Electronic. S/P: Service Platform S/P: Service Platform. SAOCOM: Satélite Argentino de Observación COn Microondas. SAR CE: SAR Central Electronic SAR: Synthetic Aperture Radar. SAR: Synthetic-Aperture Radar SIDSAR: Sistema de Ingesta Datos SAR. SIMANTSAR: Simulador de Antena SAR. SM: Structural Model SPS: Simulador Plataforma SAOCOM. SSG: Signals and Synchronisms Generator. SSR: Solid State Recorder. T: Test TBC: To be Confirmed TBD: To Be Defined TMVM: Thermal Mathematical Verification Model TRRS: Transmitter Receiver Redundancy System. TWTA: Traveling Wave Tube Amplifier. V&V: Verification and Validation


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7. DEFINITIONS Verification: is the process of demonstrating to the customer or to the relevant responsible organization that the item being supplied complies with each individual requirement defined in the governing requirement specification. The process is applied to each level of assembly. Validation: is the process of demonstrating to the customer or to the relevant responsible organization that the item being supplied fits with the Mission Requirements, the User needs and the objectives for which it is designed. This implies an assessment of whether or not the system is usable in an operational situation.

8. SAR INSTRUMENT DESCRIPTION The SAR instrument is composed by three major sub-systems:

1. The Central Electronics, 2. The SAR Antenna 3. The Data Downlink subsystem,

The SAR instrument is schematically presented in Figure 1.

Figure 1

Figure 2 shows a simplified interconnection diagram between the SAR Instrument sub-systems, and between the Instrument and the Service Platform.

Figure 2


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SAR Central Electronics (SAR CE)

SAR CE handles the complete SAR operation, the acquisition and the science data-storages and downloads to the ground station. It Generates the RF transmission/reception pulses and synchronisms, and digitalized the RF signal received by the instrument.

SAR-CE is composed of the following Sub-systems: o CDU: Control & Data Unit

o SSG: Signals & Synchronism Generator

o RTUCE: Remote Terminal Unit which provides the power supply

o CRX: Central Receiver

o TRRS: Transmit-Receive Redundancy System

o Harness: wired interconnection for power, data end RF signals

o SSR: Solid-State Recorder

o CTX: Central Transmitter

o ARB: Antenna Relay Box

SAR CE details are presented in the document “0804-RSTI-GEDCS-002 SAR CE, FUNCTIONAL DESCRIPTION”.

SAR Antenna

The SAR Antenna is an active antenna. It is full polarimetric, that means that the active front-end electronics mounted on the antenna allows amplification of the RF signal to transmit and amplify the RF signal received.

In addition the front-end allows a phase shifting and step attenuating the RF signal to be transmitted and the RF signal that is receiving. In this way is possible to change the radiation pattern of the SAR antenna in azimuth or along track. The antenna can work in horizontal, vertical or in both polarizations simultaneously.

The SAR antenna is composed of seven panels. In both sides the 3 external panels are deployable. The panels are numbered from X1 to X7 (the X4 is the central panel, fixed to the Service Platform by an Interface Structure). An schematic view of the Antenna deployment sequence is presented in Figure 3.

Figure 3

Each antenna panel includes the following assemblies or components, which can be

classified into structural components, thermal control components, deployment component, front-end electronics components and harness:

Structure and mechanisms.

Structural panels, inserts

Hinges, Latches

Restrain-Release Mechanism

Deployment Actuators

Deployment Actuators and Driver Boxes (RDADB and DADB)


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Temperature and Position Sensors

Harness

Thermal Control

Harness

Power lines and Power Junction Boxes

RF lines and Power splitter combiners

MIL-STD-1553

Deployment Harness

Thermal control Harness

Antenna thermal control

Thermal Blanket

Heaters

Thermostats

Front-end Electronics:

Transmit/Receive Assembly (CTR, "Conjunto Transmisión Recepción")

T/R Modules

Power splitter/combiners

Power supply unit

Control and 1553 communication unit

1553 micro-couplers

Harness

Thermal Control

Temperature Sensors

Radiating modules

Details about the SAR Antenna configuration are presented in the document

SAR Data Down Link (DDL)

DDL allows downloading to ground the science data gathered and stored during the SAR Instrument acquisition.

The SAR Data Downlink sub-system (DDL) consists of two chains simultaneous and redundant chains with the following components:

o Two 155.5 Mbps 4d 8psk-Tcm X-Band Modulator ;

o 2 TWTA, 34 Watts;

o High Power Omux;

o Low Gain X-Band Antenna, Quasi-Flux Type;

o Rigid And Flexible Waveguide

Figure 4 shows the current SAR DDL sub-system configuration.


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Figure 4


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9. V&V APPROACH The verification process is that part of the task within the SAOCOM SAR Instrument, which

demonstrates its conformance to the applicable requirements.

The following sections report the verification approach adopted for SAR P/L. The description includes general and specific verification guidelines, verification levels and a rationale on the verification activity monitoring and verification results management.

The main objectives of the SAR Instrument verification program are:

o To qualify the SAR Instrument design

o To ensure that the product is in agreement with the qualified design, is free from workmanship defects and acceptable for use in flight

o To verify that the SAR Instrument will be able to fulfill the mission requirements

The general approach for the verification requirements will follow statement reported here below:

Instrument specific requirements verification will be performed at the lowest possible level

verification will be performed on a model which is fully flight representative for the dedicated verification objective

the verification will be performed as far as possible by test in a most realistic environment (taking into account physical, schedule and cost constraints)

as a general rule final verification will be performed at the highest integration level, nevertheless, in order to reduce cost and schedule impacts, verification performed at lower level and fully representative will be not repeated at higher level

Existing, applicable and adequately documented qualification history of an item may be utilized for qualification for similarity.

Validation of the S/W Tools as for the SAR P/L Processor

Validation of the SAR P/L Calibration process

Software verification will always be completed by test in the real hardware environment

design change after qualification completion will require a delta qualification activity to be defined case by case


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10. VERIFICATION & VALIDATION PROCESS Verification activities are conducted across all development and integration phases of the

SAR Instrument, verification is accomplished through an integrated hierarchical approach, progressing from component to element.

Individual components shall be verified by their own providers. Throughout these lower-level verification activities, CONAE shall have insight into the verification records and reports of the items under their responsibility.

The verification activities will be incrementally performed at different levels and in different stages, applying coherent top-down (definition phase) and bottom-up (implementation phase) concepts and utilizing a suitable combination of different verification methods.

The verification process flow shall be basically subdivided in the following steps:

o Identification and classification of all the requirements to be verified

o Selection of verification criteria (e.g. methods/levels/stages) and models against identified requirements

o Establishing the planning for the associated verification activities

o CONAE’s concurrence

o identification of verification documentation

o performing of verification tasks and verification control

o completion of verification control and evidence of verification close-out

o CONAE’s review and final approval

10.1. Verification Plan Approach The verification approach herein proposed is derived in specifics verification plans, which

have to take into account the following activities:

o Identifying a consistent set of verifiable program requirements which can be subjected to the verification process;

o Selecting methods of verification;

o Selecting levels of verification and associated model philosophy;

o Selecting facilities and optimizing their utilization;

o Identifying resources required and optimizing their utilization;

o Identifying the stages and the events in which the verification is implemented.

10.2. Verification Implementation The verification plan is an iterative process; it involves all concerned parties and will be closed

only when the design is frozen, nominally at the satellite Critical Design Review (CDR).

The following general rules will be considered in implementing the verification plan program:

o Ensure a coherent approach to the verification implementation throughout the various levels in order to achieve a verified product;

o Provide adequate visibility and objective evidence of verification performed.

o Ensure the definition of correct verification criteria for each requirement by participating in the preparation of design verification documents;

o Optimize the use of test facilities;

o Ensure early verification of critical items to reduce the risks of late failure identification;


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o Optimize the design and use of ground support equipment, simulators and test software;

o Minimize cost and schedule by avoiding duplication of tasks whenever possible;

o Optimize the AIT flow and schedule to secure the master schedule and meet the major milestones;

The requirements breakdown structure is presented in Figure 5

SCIENCE

Module: L1-SR Resp: CONAE

MISSION

Module: L2A-MR Resp: CONAE

MISSION SYSTEM

Module: L2B-MSR Resp: CONAE

ENVIRONMENTAL

Module: L2B-ERDResp: CONAE

SAFETY & PRODUCT ASSURANCE

Module: L2B-SPARDResp: CONAE

SERVICE PLATFORM

Module: L3B-SPResp: INVAP

GROUND SEGMENT

Module: L3A-GS Resp: CONAE

GROUND SUPPORT EQUIPMENT

Modulo: L3-GSE

SAR INSTRUMENT

Module: L3-SAR Resp: CONAE

LAUNCH SERVICES

Module: L3A-LSResp: CONAE

ILS & OPSModule: L3A-ILSOPS

Resp: CONAE

AOCSModulo: L4-SP-AOCS

Resp: INVAP

CDHModulo: L4-SP-CDHS

Resp: INVAP

COMMUNICATIONModulo: L4-SP-COMMS

Resp: INVAP

HARNESSModulo: L4-SP-HARS

Resp: INVAP

MASS MEMORYModulo: L4-SP-MMS

Resp: INVAP

POWERModulo: L4-SP-PCS

Resp: INVAP

PROPULSIONModulo: L4-SP-PROPS

Resp: INVAP

STRUCTUREModulo: L4-SP-SMS

Resp: INVAP

THERMALModulo: L4-SP-TCS

Resp: INVAP

DATA DOWNLINK

Module: L3-SAR DDLResp: CONAE

CENTRAL ELECTRONICS

Module: L3-SAR CEResp: INVAP

SAR ANTENNA

Module: L3-SAR Resp: CONAE

SAR ANTENNASTRUCTUREResp: CNEA

SAR ANTENNACTR

Resp: CONAE

SAR ANTENNADeployment Electronics

Resp: CONAE

CDU: Control & Data Unit

SSG: Signals & Synchronism Generator

SAR CE Power:ARB: Antenna Relay Box

RTU

CRX: Central Receiver

TRRS: Transmit-Receive Redundancy System

SAR ANTENNAHarness

Resp: CONAE

Harness: wired interconnection for power, data end RF

signals

SSR: Solid-State Recorder

CTX: Central Transmitter

Figure 5


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10.3. SAR Instrument L3 Requirements Validation Process Validation process is presented in Figure 6.

Figure 6

10.4. SAR Instrument L3 Requirements Verification Process Evidence about the close-out of each L3 requirement shall be provided by the responsible, in

order to close each requirement in the RVVM, as is shown in Figure 7.

Perform SAR Intrument L3 Requirements Verification Activities

Provide Test/Analysis/Demonstration/Inspection/PCR/Verification Reports including any

required evidence that each L3 requirement has been fully Verified

Are all this children Requirement well

verified?

No

Close Verification Process for this L3 Requirement

Close in the RVVM the L3 requirement Set.

Verification close out

Yes

Issue a Nonconformance or PFR and formulate inplementation and

feedback to the appropriate point of the

process

To the Process

No

Yes

Figure 7


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11. VERIFICATION METHODS Verification can be accomplished by one or more of the following methods:

Test Analysis Similarity Inspection Demonstration

11.1. Test Verification by test is the actual operation of equipment during ambient conditions or when

subjected to specified environments to evaluate performance. The analysis of data derived from “Test” shall be considered an integral part of the test.

Two subcategories are defined:

Functional testing

Functional testing is an individual test or series of electrical or mechanical performance tests conducted on flight or flight-configured hardware and/or software at conditions equal to or less than design specifications. Its purpose is to establish that the system performs satisfactorily in accordance with design and performance specifications. Functional testing generally is performed at ambient conditions and performed before and after each environmental test or major move in order to verify system performance prior to the next test/operation.

Environmental testing

Environmental testing is an individual test or series of tests conducted on flight or flight-configured hardware and/or software to assure it will perform satisfactorily in its flight environment. Environmental tests include vibration, acoustic, and thermal vacuum and may be combined with functional testing if test objectives warrant.

11.2. Analysis When verification is achieved by performing theoretical or empirical evaluation by accepted

techniques, the method will be referred to as “Analysis”.

Verification by analysis is a process used in lieu of (or in addition to) testing to verify compliance to specifications/requirements. The selected techniques may include systems engineering analysis, statistics and qualitative analysis, computer and hardware simulations, and computer modeling. Analysis may be used when it can be determined that:

rigorous and accurate analysis is possible;

testing is not feasible or cost-effective;

similarity is not applicable and/or inspection is not adequate.

11.3. Similarity Verification by similarity is the process of assessing by review of prior acceptance data or

hardware configuration and applications is similar or identical in design and manufacturing process that has previously been qualified to equivalent or more stringent specifications.

11.4. Inspection Verification by inspection is the physical evaluation of equipment and/or documentation to

verify design features. Inspection is used to verify construction features, workmanship, and physical dimensions and condition (such as cleanliness, surface finish, and locking hardware).

When verification is achieved by visual determination of physical characteristics (such as construction features, hardware conformance to document drawing or workmanship requirements) the method will be referred to as “Inspection”.


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11.5. Demonstration Demonstration is the observation of the functional operation of the verification item in a

controlled environment to yield qualitative results without the use of elaborated instrumentation, procedures or special tests equipment.

The distinction between the demonstration method and the test method is subtle. The emphasis regarding the demonstration method is of observing the operation on the verification item that is primarily qualitative. The emphasis regarding the test method is on executing a verification that yields quantitative results. Demonstration usually does not require the use of elaborate instrumentation or special test equipment and does not necessarily generate output data or quantitative results. For commercial of the shelf hardware or of the shelf software products used in the hardware support environment, such as operating systems, demonstration is the most common verification method. The test methods always generate quantitative results, including null results. The success/failure of a verification item associated with the demonstration method can be determined by simple observation of the qualitative results. For the test method, the pass/fail criterion requires, as a minimum, a quantitative comparison.

Often requirements associated with reliability, transportability, maintainability, serviceability, and human engineering factors are verified using this method. The system elements may be instrumented with quantitative limits of performance monitored; however, only checklists are required rather than recordings of actual performance data.

11.6. Validation of records Verification by validation of records is the process of using manufacturing records at end-item

acceptance to verify construction features and processes for flight hardware.

The following considerations shall be taken into account when selecting a verification method:

All safety critical functions shall be verified by test.

Test shall be the preferred verification method when it is practical, cost effective and safe; alternative methods may be selected, considering requirement criticality, cost effectiveness and schedule.

12. VERIFICATION PHASES The verification process shall be implemented in subsequent verification phases all along the

SAR program life cycle. The verification phases are defined periods of major program activity when verification is to be accomplished. The following phases are considered in this frame:

12.1. Development The development phase is the period during which a new design or concept is initiated,

refined and implemented up to manufacturing of qualification or flight hardware. Activities during this phase will provide confidence that the new design and concepts will accomplish design requirements.

12.2. Qualification Qualification tests are formal demonstration that design, implementation, and manufacturing

methods have resulted in H/W and S/W conforming to specification requirements. Qualification is conducted at levels and duration that ensure that the production item can be subjected to acceptance when required without degradation and will perform satisfactory in the use environment with sufficient margin. Qualification H/W and S/W shall be representative of the flight. The SM and EM spacecraft’s and relevant S/S are included in this stage. Verifications during this phase are conducted on flight-quality hardware at conditions more severe than acceptance conditions to establish that the hardware will perform satisfactorily in the flight environments with sufficient margin.


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12.3. Acceptance The acceptance phase is the period during which the deliverable flight end-item is shown to

meet design and performance requirements under conditions specified for the SAOCOM mission. The acceptance phase ends with shipment of the satellite to the launch site.

Acceptance tests are the necessary formal tests conducted to demonstrate acceptability of the item for delivery. Acceptance testing consists of electrical, functional and acceptance level environmental tests to ensure compliance with the design specification. This testing is conducted to detect deficiencies in workmanship, material, and quality that may not be detected by other inspection technique.

The PM & FM items is included in this stage.

Proto-Qualification tests are to qualify the design and method of manufacture and accept it for flight operations. Qualification of design and manufacturing method is accomplished by imposing environmental levels more severe than those expected during ground and orbital operations. H/W fatigue is avoided by limiting the exposure so as not to spend a significant portion of the useful life of the H/W. They are also to detect latent material and workmanship defects and to provide experience with the test item’s performance under conditions similar to the mission environment.

12.4. Pre-launch The pre-launch phase is the period which begins with the arrival of the satellite at the launch

site and terminates at launch. Requirements verified during this phase are those which demand the integrated satellite and/or launch site facilities.

Pre-Launch tests are a subset of the tests performed as part of the qualification/acceptance program to finally demonstrate the flight worthiness. PFM through FM SAR Instrument integrated on the spacecraft’s are considered in this stage.

12.5. Flight / Mission The flight/mission phase is the period which begins at liftoff and continues through on orbit

lifetime. During this phase, the satellite shall be verified and validated to operate in space environment conditions.

13. V&V RESPONSIBILITIES

13.1. CONAE´s Responsibilities SAR Instrument Verification & Validation

SAR Instrument System Engineering

Materials Procurements

Final approval of all providing organizations V&V activities;

Integration and Test Management and Conduction.

Related with SAR Instrument Test Campaigns:

o Planning and Organization of Tests Campaigns

o Logistics

o Agreements with Test Facilities

o Test Plans Approval and Authorization

o Follow up of Test Activities

o Approval of Test Results

o Safety & Assurance during Transportation, Handling & Tests

SAR Antenna Verification.

SAR Antenna CTR Verification Approval


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SAR Instrument DDL Verification Approval

SAR Instrument CE Verification Approval

Reviews coordination and approval.

Providers Verification Plans Approval

Verification Documents Approval

SAR Instrument Interface Verification

Figure 8

13.2. Providing Organizations Responsibilities V&V responsibility is assigned to the providing organizations, which assign responsibility to

subordinate organizations or contractors through appropriate requirements documents and statements of work. Further breakdown of specific responsibilities have to be detailed in the individual element V&V plans.

Each providing organization shall elaborate, and submit to CONAE for final approval, an adequate V&V Plan for their products, in which appropriate models, verification matrixes, methods, and stages are selected.

Main providing organizations and their corresponding V&V responsibilities are:

INVAP Responsibilities:

o CE & DDL Verification Plans Elaboration

o SAR CE Verification

o SAR DDL Verification

o Associated EGSE & MGSE Verification

o EIDP Elaboration

o DDL & CE Verification Documents Elaboration

CNEA Responsibilities:

o Structure & Mechanisms Verification Plans Elaboration

o SAR Antenna Structural Verification

o SAR Antenna Mechanisms Verification

CONAE I&T Management and Conduction

Reviews coordination and Approval

Test Program Definition

Logistic Support

Agreements with Test Facilities

I&T Procedures Approval & Authorization

Approval of Test Results

Anomaly Resolution Approval

CNEA SAR Antenna S&M

Rad. Mod. MAIT

SAR Antenna MGSE

SAR Antenna I & T (Mech)

Antenna to S/P

STI

Panels Integration

Antenna harnessing

Specific GSE

INVAP

DDL I & T

SAE CE I & T

Specific GSE

GEMA

Thermal Hardware Integration

All Contractors Responsibilities

Test Results Analysis

I&T Procedures Elaboration & Execution

Support Test Conduction

Anomaly Resolutions

In house Testing

DTA

CU Developing & MAIT

CTR I & T

Specific GSE


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o Radiating Modules Structural Verification

o SAR Antenna Mechanical Interface Verification


o EIDP Elaboration.

o SAR Antenna Verification Documents Elaboration

DTA Responsibilities:

o Verification Plans Elaboration

o CTR Verification


o EIDP Elaboration.

o CTR Verification Documents Elaboration

STI Responsibilities:

o Verification Plans Elaboration

o Harness Verification

o Associated GSE Verification

o EIDP Elaboration.

o Harness Verification Documents Elaboration

GEMA Responsibilities:

o I&T Procedures Elaboration & Execution

o Support Test Conduction

o Thermal Hardware Verification Plans Elaboration

o Thermal Hardware Verification

o EIDP Elaboration.

o Thermal Hardware Verification Documents Elaboration

14. V&V DOCUMENTATION The verification process and its implementation activities shall be documented by means of a

specific set of verification documents. This activity is a compromise between minimizing documentation effort, to meet cost/schedule constraints and the requirement to properly trace the verification events, which is fundamental in order to reduce risks and to facilitate recovery actions in case of problems.

The verification process documentation is summarized in [AD5]

The main document controlling the overall V&V activities of the SAR Instrument is this plan. Each supplier must provide the documentation indicated in [AD5]. All these documentation will become part of the SAR Instrument EIDP.

14.1. Requirement Verification and Validation Matrix As required in [AD5] a Requirement Verification and Validation Matrix will be performed in

order to track all SAR Instrument L3 Requirements. An example is shown in Figure 9.

ID L3_Requirement Verification

Methods Verification Phases

Verification Levels

Verification Status

Verification Document

Comments

Requirement Level/ID

Requirement Title / Text

Figure 9 This Matrix shall be filled in the following way:

In the first column the requirement number has to be completed.

In the second column a description is included.

The Verification Methods column shall be filled with the applicable method(s).


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The Verification Phases column shall indicate when this requirement is being verified.

The Verification Levels column indicates at witch level this requirement shall be verified.

Verification Status column indicates if the requirement verification is still open, or if it has been closed. Each requirement shall be approved by CONAE before changing it status to CLOSE

In the Verification Document column the document where the item is verified should be listed (e.g. Test Report number).

The last column is to help the completion of the matrix.

14.2. Verification process and the related documentation The following figure shows the verification process and the related documentation.

Figure 10


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14.2.1. Environmental Test Authorization and Summary (ETAS) The ETAS form shall be used to summarize the environmental tests to be performed on each

testable element and to convey technical instructions to the test agency.

14.2.2. Test Specification The test specification contains the activity objectives, the selected approach, the article

configuration, the set-up description, the necessary GSE, the equipment and instrumentation, the conditions for the activity, the required facilities, the sequence of activities with the detailed verification requirements, the success criteria, the organization and responsibilities, the involved documentation, the relationship with product assurance activities, the schedule.

14.2.3. Test Procedure The test procedure shall provide detailed step-by-step instructions for conducting test

activities in agreement with the relevant test requirements.

The test procedure shall contain the activity objective, the applicable documents, the references to the relevant test specification, the participants required, the article and tools configuration list, the step-by-step procedures.

14.2.4. Test Report The test report shall describe test performance, results and conclusions in the light of the test

requirements.

This report shall contain the introduction, the test description, the test results including the as-run test procedures, the considerations and conclusions with particular emphasis on the close-out of the relevant verification requirements including any deviation.

14.2.5. Analysis Report The analysis report shall describe, for each verification analysis, the relevant assumptions,

utilized methods, techniques and results.

It shall contain proper evidence that the relevant requirements are verified and the indication of deviations.

14.2.6. Inspection Report The inspection report shall describe each verification activity performed for inspecting

hardware. It shall contain proper evidence that the relevant requirements are verified and the indication of any deviation.

14.2.7. Verification Report The verification report may be prepared in case that more than one of the defined verification

methods are utilized to verify a requirement or a specific set of requirements.

It shall explain the approach followed and how the verification methods were combined to achieve the verification objectives.

The positive achievement constitutes the completion of verification for the particular requirement.

14.2.8. Other Documents In addition to the above major documentation, other documents may be part of the verification

process to provide the necessary traceability and event record, such as: Test Configuration List (TCL), End-item Data Packages, Logbooks (including work items and deviation work items), Problems and Failure Reports (P/FRs), Nonconformance Reports (NCRs), Request for Waivers (RFWs), Manuals, Simulation Plans, Verification Tools Documentation.


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15. SAR INTRUMENT V&V STRATEGY The following strategy will be applied in order to meet the overall objectives of the verification

of the SAR Instrument:

o mechanical qualification of each equipment and subsystem

o thermal qualification of each equipment and subsystem

o ESD/EMC qualification of each electronic equipment and subsystem

o RF qualification of the concerned equipment or subsystems

o electrical functional and performance qualification of each equipment and subsystem

o on-board S/W validation

o Fitting Electrical, mechanical and thermal mathematical Models.

o certification of the compatibility of all elements of the complete SAR Instrument.

o certification of the compatibility of all elements of the complete SAR Instrument with the SAOCOM Satellites and Ground Segment.

16. QUALIFICATION AND FLIGHT MODELS

16.1. Qualification Models Qualification tests are formal demonstration that design, implementation, and manufacturing

methods have resulted in H/W and S/W conforming to specification requirements.

In this frame will be deployed the following main qualification models:

CTR

o CTR Qualification Model

o CTR EM Model

SAR ANTENNA

o SAR Antenna Structural Model

o SAR Antenna Mechanisms Qualification Models

o Radiating Module Qualification Models

o SAR Antenna Panel Thermal Qualification Model

o SAR Antenna Panel Engineering Model

o SAR Antenna Radiometric Mathematical Model

o SAR Antenna Thermal Mathematical Model

o SAR Antenna Structural Mathematical Model

SAR INSTRUMENTS

o SAR Instrument Engineering Model

o SAR CE Engineering Model.

o SAR DDL Engineering Model.


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Mecanism Qualification

Model Structural SAR Antenna Model

SAOCOM SM

Antenna DDLCentral

ElectronicsSAR Instrument Satellite

Central Electronics Eng. Model

DDL Eng.

Model

Panel EM

SAR Antenna Wing S/P SM

EM Deployment Electronics

EQM Deployment E.

Interface Structure

CTREM

TRM EM

Panel EM

CTREM

SAR Antenna SM

CTREQM

TRM EQM

Components Qualification

SAR - EM

Central Electronics EM

DDL EM

SAR Instrument EM

SAOCOM EM

S/P EM

Central Panel

Radiant Modules Qualification

Model

EMANTSAREM Panel

Figure 11

16.1.1. SAR Antenna Structural Model The SAR Antenna SM will integrate with the SM of the service platform and will test together.

This model will represent a full scale antenna structure. It will consist of one full deployable wing, a dummy wing, a central panel, and the interface structure.

All structural and mechanical components will be made with flight like materials and processes. Irradiating Modules (flight like) will be added to this model to ensure that tests environmental conditions do not degrade the performance of the antenna.

This model will be tested together with the service platform structural model for environmental and mechanical functional testing.

It will be used for;

SAR Antenna structural design qualification;

SAR Antenna Mechanism qualification;

Mathematical Structural Models adjustment;

Validation of the manufacture, production, integration, handling, transportation and functional test procedures at Subsystem level.

Verification of the mechanical interface between Service Platform and GSE.

Validation of the Ground Support Equipment.

Verify the right antenna deployment after the mechanical tests.

16.1.2. SAR Antenna Panel Thermal Qualification Model The SAR Antenna Panel Thermal Qualification Model will be a panel of the SAR Antenna

Structural Model. It will test in a solar simulator to probe the thermal control design.

After the structural model campaign one panel of it will be removed and will be tested thermally on a Solar Simulator Chamber. In addition to the requirement of the SAR Antenna Structural Model, this panel shall consist of:

All CTRs boxes and its components Structural and Thermal Dummies.

All panel harness. It included the power splitter combiner and the power junction boxes Structural and Thermal Dummies. All cables shall be Flight like


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Deployment Electronics Boxes Structural and Thermal Dummies

Connectors shall be like Flight.

MLI and its grounding

Flight painting

Thermal Gap Fillers shall be like Flight.

Heaters and thermostats shall be like Flight.

This test will be used for;

SAR Antenna thermal panel qualification;

SAR Antenna thermal hardware structural qualification.

Final Thermal Mathematical Models adjustment;

Validation of the manufacture;

16.1.3. SAR Antenna Panel Engineering Model The purpose of this model is to enable functional verification, electrical interfaces verification

and performance of the SAR Antenna at panel level. It will allow extending by analysis the performance to the Antenna Level. It will be tested with EGSE before to integrate with the SAR CE EM.

The SAR Antenna Engineer Model will be composed by:

A structural panel

CTR EM

20 LTRM EM

20 PSU EM

20 UC EM

RFDN EM

EGSE

16.1.3.1. Verification Flow

Figure 12

16.1.4. Radiometric Antenna Mathematical Model This model will represent the SAR antenna RF behavior. It model will be used to predict the

antenna radiation patters.

It model will be used in this stage to verify same antenna requirement that can’t verified by test.

FUNCTIONAL &

RF TEST

THERMAL TEST (reduced Range)

& RF TEST

FINAL RF TEST

EMC TEST

SAR ANTENNA EM PANEL TEST SEQUENCES

To SAR Instr ACTIVITIES


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16.1.5. SAR Antenna Structural Mathematical Model It will be used for:

Assist the mechanical design process during all the pre-launch activities.

Be added to spacecraft models to be used for coupled load analysis with the launcher

Predict loads during tests, transport, launch and flight environments.

16.1.6. SAR Antenna Thermal Mathematical Model It will be used for:

Assist in the mechanical and thermal design process during all activities.

Analyze the S/P - Antenna coupled behavior and verify the requirements.

16.1.7. SAR Central Electronics Engineering Model The SAR Central Electronics EM is a qualification model of the SAR central Electronics, and It

is under Invap qualification responsibility. It will test separately to prove same performance and functional requirements.

The SAR CE EM will be integrated with the SAR Instrument Model to probe functional and interface requirement.

The SAR CE details are described in the document “0804-RSTI-GEDCS-002-A SAR CE, FUNCTIONAL DESCRIPTION”. SAR-CE is composed of the following Sub-systems:

CDU: Control & Data Unit

SSG: Signals & Synchronism Generator

RTUCE: Remote Terminal Unit which provides the power supply

CRX: Central Receiver

TRRS: Transmit-Receive Redundancy System

Harness: wired interconnection for power, data end RF signals

SSR: Solid-State Recorder

CTX: Central Transmitter

ARB: Antenna Relay Box

16.1.8. SAR DDL Engineer Model The DDL EM will be integrated with the SAR Instrument Model for qualification of functional requirements. For more information regarding this model, see [RD23].

16.1.9. SAR Instrument Engineering Model (EM) The SAR Instrument EM will be used to verify the compliance of the functional and

performance requirements.

The SAR Instrument EM will be used for:

Electrical I/Fs verification (Power, 1553, RF) o Verify electrical interfaces among the subsystems of the Central Electronics

o Verify the interfaces between the service platform simulator and the Central Electronics

o Verify the electrical interfaces between the Central Electronics and the SAR antenna

o Verify the electrical interfaces between the Central Electronics and the Data Download system


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o Verify the SAR Instrument harness at all levels

o Power Bus verification (In-Rush, PRF Ripple, Consumption)

Validate functional design at each level

Validate instrument-ground segment interfaces

Validate integration sequences and procedures

Validate functional test and test procedures

SAR operation verification.

Beam Forming verification in Near Field facility

RF parameters verification

SAR Central Electronics debugging and design qualification.

Hardware and software functional debugging and functional design qualification, including EGSE.

End to End and functional and performance product validation against SAR applicable L3 requirements, will be performed at different levels, with GSEs and specific instruments & BTEs

Operators training

EMC/ESD Verification

ISAR Test (out-doors test)

The EM will be electrically representative of Flight Models and will be composed by:

SAR Antenna Panel EM

Central Electronics EM

DDL EM

EMANTSAR

SAR Antenna Emulator (EMANTSAR) The EMANTSAR is a hardware intended to simulate the SAR Antenna and terrain behavior. It

will be connected to the Central Electronics EM/PFM/FM (depending on the qualification stage) to allow an on ground CE functionality/performance verification.

It model is not a qualification model by itself, but will be compose the SAR instrument qualification model in order to prove same functional requirements.

16.1.9.1. Verification Flow

SAR CE EM FROM

AIT ACTIVITIES

SAR ANTENNA EM PANEL FROM AIT

ACTIVITIES

EMSAR Instr.

INTEGRATED TEST

EM SAR Instr. EMC TEST

DDL EM S/S FROM

AIT ACTIVITIES

EM SAR Instr.

OUT‐DOOR TEST


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Figure 13

16.2. Proto-Flight & Flight Models The Proto-Flight and Acceptance phases are the period during which the deliverable flight

end-item is shown to meet design and performance requirements under conditions specified for the SAOCOM mission. The Proto-Flight and the Acceptance phase ends with shipment of the satellite to the launch site.

Proto-Flight and Acceptance tests are the necessary formal tests conducted to demonstrate final acceptability of the item for delivery. Proto-Flight and Acceptance testing consists of electrical, functional and acceptance level environmental tests to ensure compliance with the design specification.

There are two flight models:

SAR Instrument Proto-flight Model (SAOCOM 1A) where is composed by a PFM and FM Elements/units

SAR Instrument Flight Model (SAOCOM 1B) where is composed only by a FM Elements/units

SAOCOM 1A

SAR Antenna PFM

Central Electronics

PFM DDL PFM

SAR Antenna FM

Central Electronics

FM

DDL FM

SAR Inst. - PFM

SAR Antenna PFM

Central ElectronicsPFM

DDL PFM

SAR Inst. - FM

SAR Antenna FM

Central Electronics FM

DDL FM

S/P PFM

SAR Instrument PFM

SAOCOM 1B

S/P FM

SAR Instrument FM

Antenna DDLCentral

ElectronicsSAR Instrument Satellite

Figure 14


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16.2.1. Verification Flow

Figure 15

16.2.2. Proto-flight Model This model will be the first SAR Instrument built with all Flight qualified components; it will be

built and tested as a Proto-flight component. One complete unit will be fully assembled and integrated with the satellite and then its mechanical function will be tested at this level, after which it will be tested at proto-flight levels.

This Proto-flight model will be tested in accordance with the environmental test specification, consistent with the launch vehicle Proto-flight test requirements (ERD), and will be used for SAOCOM 1A Satellite.

The SAR PFM will be used for the verification of functional electrical interface aspects combined with qualification of environmental aspects on real flight HW & SW. Thermal vacuum, vibration and shock test to be performed at Proto-flight levels and duration, according with applicable guides in “SAOCOM L2B Environmental Requirements”.

Flight Standard parts will be used. CONAE will apply configuration control and as-build status reporting to the FM.

It consists of:

SAR Central Electronics PFM

SAR antenna PFM

SAR DDL PFM

SAR Instrument at Spacecraft Level: During the integration of the SAR Instrument to the SP and the pre-launch activities, the SAR Instrument and SP compatibility will be verified.

16.2.3. Flight Model One SAR Instrument FM will be built and tested as a Flight component. One complete unit will

be installed over the Service Platform and tested for flight.

This Flight model will be tested in accordance with the environmental test specification, consistent with the launch vehicle Flight test requirements (ERD), and will be used for SAOCOM 1B Satellite. All components materials and processes to be used in this model are Flight qualified.

Thermal vacuum, vibration and shock test to be performed at acceptance levels and duration, according to applicable guides in “SAOCOM L2B Environmental Requirements”.

SAR CE PFM & FM FROM

AIT ACTIVITIES

SAR ANTENNA PFM & FM

PANEL FROM AIT ACTIVITIES

PFM & FM SAR Instr.INTEGRATED TEST

PFM & FM SAR Instr. EMC TEST

(Omly RE for FM)

DDL PFM & FM S/S FROM

AIT ACTIVITIES


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The Flight Models will be built to full flight standard in accordance to the PA requirements for Flight Models. Flight Standard parts will be used.

It consists of:

SAR Central Electronics FM

SAR antenna FM

SAR DDL FM

17. Verification Matrix for SAR Instrument Models

The complete V&V Matrix can be found on Annex A


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System Sub-Systems Assembly Panel Component/Unit

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SAR Instrument EM EM - - - - - - - - - - - - - - - - T T T T T T T T T T T T - T T - T T T T T T - -

SAR CE Engineering Model 1 EQM - - - - - - - - - - - - - - - - T T T T T - T T T T T - T T T - - - - - - T - -

SAR DDL Engineering Model 1 EQM - - - - - - - - - - - - - - - - T T T T T - T T T T T T T - T - T - - T - A - -

EMANTSAR 1 MM - - - - - - - - - - - - - - - - T T T T - - - - - - - - - T T - - - - - - - - -

SAR Antenna Panel Engine Panel 1 EM - - - - T T T - - - - - - - - - T T T T T T T T T T T T T T T T T T T - - - - -

Radiant Modules 20 EM - - - T T T T - - - - - - - - - - - - T - - - - - - T - - - - - - - - - - - - -

Substrates 1 EM - - - T T T - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Harness 1 Set EM - - - T T T - - - - - - - - - - - - - - - - - - - - - - - T - - - - - - - - - -

CTR 4 EM - - - T T T - - - - - - - - - - T T T T T T T T T T - - - T - - - - - - - - - -Deployment Actuator

Drive Box 1 EM - - - T T T - - - - - - - - - - - - - - T T T - T - - - - - - - - - - - - - - -

PJB 1 EM - - - T T T - - - - - - - - - - - - - - T - T - - - - - - - - - - - - - - - - -

PSC 2 EM - - - T T T - - - - - - - - - - - - - - T - T - T - - - - T - - T - - - - - - -

SAR Antena SM (1 Wing and Central Panel) SM T T T T T T T A T T T - T T T - - - - - - - T - - - T - - - - - - - - - - - - -

Integrated Wing Lateral Panels( X5-7) 1 SM T T A T T T T A T T T - T T T - - - - - - - T - - - T - - - - - - - - - - - - -

Lateral Panel ( X5) 1 SM T T A T T T T A T - - T - - - - - - - T - - T - - - T T - - - - - - - - - - - -

Lateral Panel ( X6) 1 SM T T A T T T T A T - - T - - - - - - - T - - T - - - T T - - - - - - - - - - - -

SAR Antenna Panel Thermal Qua 1 STM T T A T T T T A T - - T - - - - T T - T - - T - - - T T - - - - - - - - - T T T

CTR 4 STM T T - T - T T A - - - - - - - A A - - T - - - - - - - - - - - - - - - - - - - -

Deployment Actuator Drive 1 STM T T - T - T T A - - - - - - - A A - - T - - - - - - - - - - - - - - - - - - - -

PJB 1 STM T T - T - T T A - - - - - - - A A - - T - - - - - - - - - - - - - - - - - - - -

PSC 2 STM T T - T - T T A - - - - - - - A A - - T - - - - - - - - - - - - - - - - - - - -

Radiant Modules 20 SM T - - T - T T A - - - - - - - - - - - T - - T - - - T - - - - - - - - - - - - -

Substrates 1 SM T T - T T T T A - - - - - - - A - - - - - - - - - - - - - - - - - - - - - - - -

Harness 1 Set Dumm T - - T - T - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Thermal Hardware 1 Set STM T - - T - T - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Central Panel + IS 1 SM T T A T T T T A T - - T - - - - - - - T - - T - - - T T - - - - - - - - - - - -

Central Panel 1 SM T T A T T T T A T - - T - - - - - - - T - - T - - - T T - - - - - - - - - - - -

Radiant Modules 20 SM T - - T - T T A - - - - - - - - - - - T - - T - - - T - - - - - - - - - - - - -

Substrates 1 SM T T - T T T T A - - - - - - - A - - - - - - - - - - - - - - - - - - - - - - - -

Harness 1 Set Dumm T - - T - T - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

CTR 4 Dumm T T - T - T T A - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Deployment Actuator Drive 1 Dumm T T - T - T T A - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

PJB 1 Dumm T T - T - T T A - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

PSC 2 Dumm T T - T - T T A - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Interface Structure T A A T - T T - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Mechanisms - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

RR 6 EQM T - - T T T - - T - - T - A T(2) A T T - T - - T - - - - - - - - - - - - - - A - -

Hinges 8 EQM T - - T - T T - T - - T - - T - - - - - - - - - - - - - - - - - - - - - - A - -

Cable Support 6 EQM T - - T - T T - T - - T - - - - - - - - - - - - - - - - - - - - - - - - - A - -

Latch 6 EQM T - - T - T T - T - - T - - T - - - - - - - - - - - - - - - - - - - - - - A - -

Motor 3 FM T - - T T T T - T - - T - A T A T T - T - - T - - - - - - - - - - - - - - A - -

Antenna Dummy T T A T T T T A T - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

ELECTRICAL THERMALMODEL Level

QTY Type

MECHANICAL


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SAR Instrument FM 1 FM T(1) T(1) T(1) T(1) T(1) T(1) T(1) A T(1) T(1) A - T(1) T(1) T(1) A T T T T T - T T T T T A - T A - A - - T(1) - T(1) T(1) -

SAR CE 1 FM T T - T - T T A T - - T - A - A T T T T T - T T T T T - T T - - - - - - - T T(1) -

SAR DDL 1 FM T T - T - T T A T - - T - A - A T T T T T - T T T T T T T - - T - - - - T(1) T(1) -

SAR Antena 1 FM - - - - - - - - - - - - - - - - - - - - - - - - - A A A - - A T A - - - - A - -

Integrated Wing Lateral Panels (X1-3) 1 FM - - - T T - T A - - - - - - T A - - - T T - T - - T T T - - A T A - - - - - - -

Lateral Panels ( X1) 1 FM T T A T T T T A T - - T - - - - - - - T T - T - - T T T - T T T T T - - - T T -




Lateral Panel ( X5) 1 FM T T A T T T T A T - - T - - - - - - - T T - T - - T T T - T T T T T - - - T T -



Central Panel + IS 1 FM - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Central Panel (X4) 1 FM T T A T T T T A T - - T - - - - - - - T T - T - - T T T - T T T T T - - - T(1) T -

Interface Structure 1 FM T A A T - T T - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Mechanisms 1 Set FM T - - T T T - - T - - T - A T A T T - T - - T - - - - - - - - - - - - - - A - -

SAR Instrument PFM 1 PFM T(1) T(1) T(1) T(1) T(1) T(1) T(1) A T(1) T(1) A - T(1) T(1) T(1) A T T T T T - T T T T T A - T A - A - - T(1) - T(1) T(1) -

SAR CE 1 PFM T T - T - T T A T - - T - A - A T T T T T - T T T T T - T T - - - - - - - T T(1) -

SAR DDL 1 PFM T T - T - T T A T - - T - A - A T T T T T - T T T T T T T - - - T - - - - T(1) T(1) -

SAR Antena 1 FM - - - - - - - - - - - - - - - - - - - - - - - - - A A A - - A T A - - - - A - -





Integrated Wing Lateral Panels (X5-7) 1 PFM - - - T T - T A - - - - - - T A - - - T T - T - - T T T - - A T A - - - - - - -

Lateral Panel ( X5) 1 PFM T T A T T T T A T - - T - - - - - - - T T - T - - T T T - T T T T T - - - T T -



Radiant Modules 20 FM T - - T - T T A - - - - - - - - - - - T - - T - - - T - - - - - T - - - - - - -

Substrates 1 FM T T - T T T T A - - - - - - - A - - - - - - - - - - - - - - - - - - - - - - - -

Harness 1 Set FM T - - T T T - - - - - - - - - - - - - - - - - - - - - - T T - - - - - - - - - -

CTR 4 FM T T - T - T T A T - - T - A - A T T T T T T T T T T - - T T - T T - - - - T T -

Deployment Actuator Drive Box 1 FM T T - T - T T A T - - T - - - A - - - - - - - - - - - - T - - - - - - - - - - -

PJB 1 FM T T - T - T T A T - - T - - - A - - - - - - - - - - - - T - - - - - - - - - - -

PSC 2 FM T T - T - T T A T - - T - - - A - - - - - - - - - - - - T T - - T - - - - - - -

Thermal Hardware 1 Set FM T - - T - T - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Central Panel + IS 1 FM - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Central Panel (X4) 1 PFM T T A T T T T A T - - T - - - - - - - T T - T - - T T T - T T T T T - - - T(1) T -

Interface Structure 1 PFM T A A T - T T - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

Mechanisms - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

RR 12 PFM T - - T T T - - T - - T - A T A T T - T - - T - - - - - - - - - - - - - - A - -

Hinges 12 PFM T - - T - T T - T - - T - - T - - - - - - - - - - - - - - - - - - - - - - A - -

Cable Support 12 PFM T - - T - T T - T - - T - - - - - - - - - - - - - - - - - - - - - - - - - A - -

Latch 12 PFM T - - T - T T - T - - T - - T - - - - - - - - - - - - - - - - - - - - - - A - -

Motor 6 PFM T - - T T T T - T - - T - A T A T T - T - - T - - - - - - - - - - - - - - A - -

ELECTRICAL THERMALMODEL Level

QTY Type

MECHANICAL


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QTY Type Mas

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CTR 2 EQM T T A T T T T A T - T T - A - A T T T T T T T T T T - - - - - T T - - - - T - -

CTR 4 EM - - - - - - - - - - - - - - - - T T T T T T T T T T - - - - - T T - - - - - - -

Radiant Modules 4 EQM T T A T T T T A T T T T - - - A - - - - - A T T T T T T - - - - T T - - - T - T

Radiant Modules EM - - - - - - - - - - - - - - - - - - - - - A T T T T T T - - - - T T - - - - - -

SAR Antenna Deployment Mechanism Qualification Models EQM T T A T T T T A T T T T - T T(3) A T T - T - - T - - - - - - - - - - - - - - T - -

SAR Antenna Radiometric Mathematical Model 1 MM - - - - - - - - - - - - - - - - - - - - - - - A A A A A - - A A A A A - - A A A

SAR Antenna Thermal Mathematical Model 1 MM - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - A A A

SAR Antenna Structural Mathematical Model - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

FEM Model 1 MM A A A - - A A A A A A A A A A - - - - - - - - - - - - - - - - - - - - - - - - -

CAD Model 1 MM A A A A - A A - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

OTHER MODELS

Mathematial Models

MODEL Level MECHANICAL ELECTRICAL THERMAL

(1) At satellite level (2) Only one Unit (3) Include Life Test


35 de 40

18. TEST FACILITIES The following test facilities are required throughout the qualification campaign:

18.1. Environmental Test Facilities These test facilities include, but are not limited to, vibration, acoustics, EMI/EMC and thermal-

vacuum capabilities. SAR Instrument Flights Models will be tested integrated to the Service Platform.

For testing the lower assemblies of the antenna the INVAP, LIT, CONAE or CNEA Test Facilities will be used.

18.2. Integration, Assembly, and Test SAR Instrument assembly facilities will have the capabilities to support the antenna panels

integration. They will be clean to Class 100,000 per FED STD-209 or equivalent. Support systems interfacing with flight hardware must meet Project requirements for FMEA and proof loading.

All antenna panels’ integration will be done in CONAE Facilities. Antenna wings will be integrated at CNEA Facilities. Finally the SAR Instrument as whole will be integrated at INVAP facilities.

18.3. Other Argentine Facilities o Contractors and Subcontractors Development Labs


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ANNEX A: Complete V&V Matrix


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