UKube-1 Platform Design. Craig Clark

Transcription

1 UKube-1 Platform Design Craig Clark

2 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 technology 2. Demonstrate useful science on a CubeSat sized spacecraft 3. Demonstrate industry and university cooperation 4. Demonstrate education and outreach in STEM subjects 5. 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.

3 Payloads CMOS Imager demonstrator (Open University) variety of imaging tasks taking pictures of the earth experimental test-bed for radiation damage effects in space.

4 Payloads Janus (EADS Astrium) Random Number Generator using Single Event Upsets Based on an FPGA

5 Payloads TOPCAT (University of Bath) Topside Ionosphere Computer Assisted Tomography Uses GPS delay to map the ionosphere

6 Payloads mypocketqub (UKSEDS) A pocket satellite OpenSpace365 - Arduino Orbitview (popout camera) SuperLab - superconductors SuperSprite satellite on a chip with a UHF downlink Yes a nanosatellite inside a cubesat with another picosatellite inside that

7 Payloads FUNCUBE (AMSAT-UK) A Funcube satellite minus the platform Pretty much the same capabilities as Funcube Transponder Beacon etc.

8 Payload Development Novel approaches to spacecraft to payload integration to reduce schedule. Platform emulator.

9 Configuration Additional spoiler to aid in deorbit and equalise power in pitch spin

10 Systems

11 Mechanical layout

12 CSK PC/104 format Based upon industry standard PC/104 cards for electronic industry Daughter Board(s) CSK PC/104 Header Motherboard CSK PC/104 Standoffs

13 Solar arrays

14 ADCS Architecture

15 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

16 Mission Interface Computer

17 SA-MIC Performance Clock Primary: 20 MHZ 40 MHz [Optional] Dual Independent Redundant Processing High-performance 32-bit ARM Cortex-M1 Primary Processor Low-power 16-bit TI MSP430 Secondary Processor 350 MHz flexible processing fabric Interfaces Low-Speed I2C Platform Bus 400 kbps Low-Speed I2C Payload Bus 400 kbps High-Speed SPI Payload Bus 1 Mbps High-Speed Serial UART Communications Bus 1000 kbaud Memory Primary Processor Mass Storage: 2 GB 16 GB [Optional] ECC Protected Dual or Redundant RAM: 8 MB 16/ 32/ 64 MB [Optional] EDAC Protected ROM: 256 KB Secondary Processor Configuration Storage: 8 MB 16 MB [Optional] RAM: 16 KB ROM: 256 KB System: Platform Storage: 8 KB

18 Software Ground Station Interface Layer Control Layer Scheduler - Task 4 Script Processing Layer - Data Server Layer Fault Detection Layer Hardware API & Drivers Platform Hardware Interface Platform Subsystem Layer Spacecraft Application Layer Payload Hardware Interface Payload Subsystem Layer

19 Communications UVTRX is the primary link for data STX is a secondary link for data FUNTRX provides backdoor to MIC & platform

20 Spacecraft antennas VHF/UHF S-Band

21 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

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

23 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 POD 1. Separation microswitches detect deployment 2. 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 capture 4. Capture images (with C3D imager) 3. Wait (+ 5 min) 1. Deploy antenna 2. Activate beacon 3. Deploy solar arrays 4. Initiate roll, yaw rate damping (Bdot) 4. Initial spin mode (> 20 min, < 1 day) 1. Continue rate damping 2. Establish ground contact 5. Initial health check-out report 6. Estimate reference orientation 1. 2-axis (invert) magnetic estimate 2. Feedback estimate and current sense 3. Ground provide attitude reference 7. Stand-by mode 8. Nominal mission operations

24 Operation modes

25 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

26 Mission Status Delta CDR end of October EVT Early 2012 Launch mid-2012.

27 questions? facebook.com/clydespace twitter.com/clydespace Linkedin groups: cubesats