ukube-1 platform designmstl.atl.calpoly.edu/~bklofas/presentations/summerworkshop2011/... · •...

17 August 2011 © Clyde Space Ltd 2011

UKube-1 Platform Design

Craig Clark


Ukube-1 Background• Ukube-1 is the first mission of the newly formed UK Space Agency • The UK Space Agency gave us 5 core mission objectives:

1. Demonstrate new UK space technology2. Demonstrate useful science on a CubeSat sized spacecraft3. Demonstrate industry and university cooperation 4. Demonstrate education and outreach in STEM subjects5. Demonstrate Payload KO to flight spacecraft in <12 months

• Platform requirement to support at least 3 Primary Payloads– UKube-1 has 5 payloads

• Ukube-1 is the first mission of the newly formed UK Space Agency • Ukube-1 platform is being developed by Clyde Space and University of

Strathclyde.


Payloads

CMOS Imager demonstrator (Open University)

• variety of imaging tasks– taking pictures of the earth– experimental test-bed for

radiation damage effects in space.


Payloads

Janus(EADS Astrium)• Random Number

Generator using Single Event Upsets– Based on an FPGA


Payloads

TOPCAT(University of Bath)• Topside Ionosphere

Computer Assisted Tomography – Uses GPS delay to map the

ionosphere


Payloads

myPocketQub(UKSEDS)• A pocket satellite

– OpenSpace365 - Arduino– Orbitview (popout camera)– SuperLab - superconductors– SuperSprite – satellite on a chip

with a UHF downlinkYes – a nanosatellite inside a cubesat with another picosatellite inside that


PayloadsFUNCUBE (AMSAT-UK)• A Funcube satellite minus the

platform– Pretty much the same capabilities

as Funcube• Transponder• Beacon etc.

• http://www.funcubedongle.com/


Payload Development

• Novel approaches to spacecraft to payload integration to reduce schedule.

• Platform emulator.


Configuration• Additional spoiler to aid in deorbit and

equalise power in pitch spin


Systems


Mechanical layout


CSK PC/104 format

Daughter Board(s)

CSK PC/104 Header

CSK PC/104 Standoffs

Motherboard

Based upon industry standard PC/104 cards for electronic industry


Solar arrays


ADCS Architecture


Command and Data Handling Architecture

• MIC-FPGA master of all buses in nominal cases

• MIC-SP master of I2C buses in safe mode

• UVTRX placed on UART to MIC-SP / MIC-FPGA– Duplex communications

with transceiver

• Other signals– 1 Hz Synchronisation Pulse– STX Receive Ready– FUNTRX TC Waiting


Mission Interface Computer


SA-MIC Performance

Processing High-performance 32-bitARM Cortex-M1 Primary Processor

Low-power 16-bit TIMSP430 SecondaryProcessor

350 MHz flexibleprocessing fabric

Interfaces Low-Speed I2C

Platform Bus400 kbps

Low-Speed I2CPayload Bus400 kbps

High-Speed SPIPayload Bus1 Mbps

High-Speed Serial UARTCommunications Bus1000 kbaud

Memory Primary Processor

Mass Storage: 2 GB 16 GB [Optional]ECC ProtectedDual or Redundant

RAM: 8 MB16/ 32/ 64 MB [Optional] EDAC Protected

ROM: 256 KB

Secondary ProcessorConfiguration Storage: 8 MB

16 MB [Optional]RAM: 16 KBROM: 256 KB

System:Platform Storage: 8 KB

Clock Primary: 20 MHZ

40 MHz [Optional] Dual IndependentRedundant


SoftwareGround Station Interface Layer

Control Layer

Scheduler - Task 4 Script Processing Layer -

Data Server LayerFault Detection Layer

Hardware API & Drivers Spacecraft Application Layer

Platform Hardware Interface

Payload Hardware Interface

Platform Subsystem Layer Payload Subsystem Layer


Communications • UVTRX is the

primary link for data

• STX is a secondary link for data

• FUNTRX provides backdoor to MIC & platform


Spacecraft antennas

S-Band

VHF/UHF


Mission timeline

• Operations will follow a predefined baseline operations schedule in preliminary mission operations

• Operations will be more open in the nominal mission, with new schedules uploaded to the satellite

• End of life operations, may see satellite handed over to AMSAT-UK until inoperative


Mission orbit

• Baseline 650 km sun-synchronous 11:00 LTAN• Eclipse period lasts 33 min of 98 min orbit


Launch & early operations• Integrated into POD armed up to 120

days before launch with RBF removed• Launched as payload-of-opportunity

into LEO by Dnepr or PSLV (Russia or India)

1. Deployment from POD1. Separation microswitches detect

deployment2. Interfaces PCMs with battery and

BCRs 2. CDH initialisation

1. Check-out to separation mode (nominal)

2. Separation mode (+0 min)3. Attitude sensor data capture4. Capture images (with C3D imager)

3. Wait (+ 5 min)1. Deploy antenna2. Activate beacon3. Deploy solar arrays4. Initiate roll, yaw rate damping (B-

dot)4. Initial spin mode (> 20 min, < 1 day)

1. Continue rate damping2. Establish ground contact

5. Initial health check-out report6. Estimate reference orientation

1. 2-axis (invert) magnetic estimate2. Feedback estimate and current

sense3. Ground provide attitude reference

7. Stand-by mode8. Nominal mission operations


Operation modes


Mission operations• Primary payload operations in sunlight only

– Payloads scheduled in repeating cycle by orbit number– Dependent upon power levels, eclipse operations may be permitted

later in the mission– All operations managed by Mission Interface Computer, with power

switched on the Power Distribution board• FUNCube education transmissions in sunlight and

transponder in eclipse– Direct transmissions into classrooms with the equipment– Variations in the above will be controlled by AMSAT-UK in nominal

operations• Packet transmissions of Platform / Payload data over

nominated ground stations using UV or S-band links– depending upon specific ground station capabilities– coordinated by Primary Ground Station, files shared online


Mission Status

• Delta CDR end of October 2011.• EVT Early 2012• Launch mid-2012.


questions?

www.clyde-space.com facebook.com/clydespacetwitter.com/clydespaceLinkedin groups: cubesats

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