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17 August 2011 © Clyde Space Ltd 2011
UKube-1 Platform Design
Craig Clark
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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.
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Payloads
CMOS Imager demonstrator (Open University)
• variety of imaging tasks– taking pictures of the earth– experimental test-bed for
radiation damage effects in space.
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Payloads
Janus(EADS Astrium)• Random Number
Generator using Single Event Upsets– Based on an FPGA
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Payloads
TOPCAT(University of Bath)• Topside Ionosphere
Computer Assisted Tomography – Uses GPS delay to map the
ionosphere
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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
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PayloadsFUNCUBE (AMSAT-UK)• A Funcube satellite minus the
platform– Pretty much the same capabilities
as Funcube• Transponder• Beacon etc.
• http://www.funcubedongle.com/
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Payload Development
• Novel approaches to spacecraft to payload integration to reduce schedule.
• Platform emulator.
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Configuration• Additional spoiler to aid in deorbit and
equalise power in pitch spin
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Systems
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Mechanical layout
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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
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Solar arrays
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ADCS Architecture
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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
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Mission Interface Computer
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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
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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
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Communications • UVTRX is the
primary link for data
• STX is a secondary link for data
• FUNTRX provides backdoor to MIC & platform
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Spacecraft antennas
S-Band
VHF/UHF
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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
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Mission orbit
• Baseline 650 km sun-synchronous 11:00 LTAN• Eclipse period lasts 33 min of 98 min orbit
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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
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Operation modes
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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
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Mission Status
• Delta CDR end of October 2011.• EVT Early 2012• Launch mid-2012.
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questions?
www.clyde-space.com facebook.com/clydespacetwitter.com/clydespaceLinkedin groups: cubesats