Design, Testing and Integration of Small Satellites The AraMiS experience

Transcription

1 Design, Testing and Integration of Small Satellites The AraMiS experience Dr. Muhammad Rizwan Mughal Institute of Space Technology, Islamabad

2 A Few Motivations Actual satellite technologies lead to high costs for space missions The use of COTS reduces development time and cost Reduced reliability of COTS can be compensated by proper design and redundancy Modularity helps: to share costs among multiple missions; to reduce manufacturing and testing costs to easily increase redundancy 2/19

3 Exploring innovative design techniques Innovation drivers: Low cost (use of COTS) High Rel (use of appropriate design tech) Simple to develop (accessible to single students) Simple to test and qualify (to be affordable) Highly reusable Highly redundant Components and techniques from automotive Integration phase must be simple 3/19

4 Design Innovations: plug&play A subsystem (to be plugged) A host (to plug into) important: one architecture or more? A list of functions (commands) available to the user A (set of) driver(s) to properly operate Specifications (electrical, functional, requirements, etc.) Maintenance instructions Design documentation Configuration storage host memory 4/19

5 The AraMiS approach to P&P! Take the best of P&P and design a whole new design approach around it!!! 5/19

6 First ARAMIS Concepts - Tiles Power Management and AOCS Tiles Payload OBC and TT&C Tile 6/19

7 Modular Architecture - Assembly 7/19

8 Configurations High level of integration on Tiles Compact stack of different materials and resins designed taking into account inspection Tiles can be arranged in a variety of configurations 8/19

9 Configurations Rectangular Box 20 PMT; 2 TTC Up to cm 2 payload-specific openings Hexagonal prism with 20 cm optical telescope payload Solar Panels array MOCKUP 9/19

10 The new AraMiS frontier Pushing the concepts of modularity and P&P to the limit Reducing module granularity to the minimum 10/19

11 AraMiS AraModules and Tiles An AraModule is a tiny P&P subsystem 11/19

12 AraMiS AraModules and Tiles BUT an AraModule is a SMALL logical subsystem 12/19

13 AraMiS P&P Step 1 a) select processor from a library b) add to virtual board AraModules PROC BOARD 13/19

14 AraMiS P&P Step 2 a) select power supply from a library b) add to virtual board PROC PS BOARD 14/19

15 AraMiS P&P Step 3 a) select AOCS sensors and actuators b) add to virtual board PROC PS S&A BOARD 15/19

16 AraMiS P&P Step 4 select and add: a) RF module(s) b) antenna(s) c) Other sensors d) On-board modules e) Payload support f) Any other PROC S&A PS RF ANT MOD1 MOD2 BOARD 16/19

17 AraMiS P&P Step 5 (proto) a) take corresponding proto modules b) assemble to proto system Connector PEM Spacer Module Motherboard PROTO BOARD Double Module QuadrupleModule Single Module 17/19

18 AraModules - II

19 AraMiS P&P Step 6 (assemble SW) a) take associated SW drivers b) generate C code c) compile 19/19

20 AraMiS P&P Step 7 a) Test b) Validate HW & SW c) Virtual deploy 20/19

21 AraMiS P&P Step 8 a) Select thermomechanical support b) Assemble schematics c) Create an ad-hoc PCB d) Assemble components e) Load SW f) Get functional system!!! g) We call them Tiles h) In just a few weeks!!! 21/19

22 Spacecraft Configurations Design the new subsystems either on single, double or quadruple module configuration. Test the subsystems on ground using development board. Integrate each physical module in a physical module based satellite configuration. Embed the logical modules in the main tile for a Satellite on demand configuration. The Satellite on demand configuration can be altered very easily for Reusable design configuration Small Satellite Engineering and Design Workshop 3 Dece 22 mber 2015

23 Physical Module Based Configuration Develop standard tiles hosting multiple connectors Physical daughter boards connected to the tile via pluggable connectors The subsystem module only plugged if mission needs it. High level of design flexibility, testability and upgradability Testing of modules, tiles and whole satellite is needed For teaching/research purposes Small Satellite Engineering and Design Workshop 3 Dece 23 mber 2015

24 Satellite on demand Configuration Already tested modules integrated inside the PCB. Reusability of physical subsystem modules Permanent configuration Testing of modules: not required Testing of tiles and mission is required only CubeSat standard tile built using this approach Small Satellite Engineering and Design Workshop 3 Dece 24 mber 2015

25 Reusable design configuration Optimised spacecraft configuration based on customer requirements Reuse of the satellite on demand configuration Minor addition or removal of subsystems on customer demands Follows the Cheaper-Faster-Better philosophy Module and tile testing: not required Only mission testing is needed for this configuration Small Satellite Engineering and Design Workshop 3 Dece 25 mber 2015

26 Design trade off Small Satellite Engineering and Design Workshop 3 Dece 26 mber 2015

27 CubePMT: Solar Panel Side 27

28 CubePMT: Component Side 5 pins I2C Connector Magnetometer 3.3V Switching Regulator 5V Switching Regulator Magnetorquer Driver J-Tag 15 pins analog connector Tile Processor Module Calibration Memory 15 pins digital connector 4 pins power connector 3V Linear Regulator 3.3V Linear Regulator Bidirectional Load Switch Temperature Sensor Boost Converter Gyroscope Current Sensor

29 CubePMT A predefined Tile CubePMT is CubeSat standard Power Management Tile Dimensions 98 x 82.5 mm 2 & 1.6 mm thickness It is an 8-layers PCB On top layer : Solar panel and sun sensor Bottom layer : electronic of EPS and ADCS subsystems Magnetorquer coil embedded in four internal layers Goals Implement all the subsystems on a single Module Increase efficiency of EPS Reduce the overall cost, weight, size and power consumption COTS 29

30 CubePMT: Block Diagram 30

31 AraMiS P&P Step 9 Build whole satellite: a) Select existing Tiles b) Develop non existing Tiles c) Integrate satellite d) Test and qualify e) Launch and operate 31/19

32 Larger Tiles

33 AraMiS CubeSats - Aramis C1

34 Smart Harness: UML Life Cycle Design Schematics D R1 IRF7324 Q1 notset G R33R RS_ R9 V S+ S REF C12 DK_ ND I N+ R3 R200R C10u V bridge A NC D C15 IRF7324 Q1 G NC R4 R3K3 RS_ V bridgeb O FFS ET +A SEN_HMC1002 RGI N- R10 R1K RS_ RG+ RS_ R1K RS_ U2 OU T R7 R1K RS_ MAGN_X K OA_AD623ARZ O U T +A D1 CZRU52C3 Documentation A O FFS ET -A V S- S/R+A OU T - A C470n DK_ ND S/R-A NC O FFS ET +B NC O FFS ET -B O U T +B S/R+B R2 IRF7311 Q11 G R33R RS_ V S+ GND2B R5 R3K3 RS_ REF I N+ I N- R12 R1K RS_ RG+ RG- R6 RS_ U3 OU T R8 R1K RS_ MAGN_Y K OA_AD623ARZ D2 CZRU52C3 A S V S- D Q11 IRF7311 RESET GND2A D R1K OU T - B S/R-B GND1A C470n DK_ ND U1 GND-PLN C14 GND1B S G S 12/3/2015 PhD Presentation 34

35 Thank You Questions? 35/19

36 ARAMPAK

37 A Few Motivations A 3U experimental cube sat to be developed jointly by Politecnico di Torino, Italy and IST, Pakistan for educational/ experimental purposes. The purpose of the design and launch is the technology transfer to IST and launch experience of AraMiS satellites. 37/19

38 The Architecture of ARAMPAK will be based on the modular and flexible panel bodies The Modules shall be designed, tested and integrated in house The design and testing requires a large number of tools and soft wares 38

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40 Subsystem Classification 40

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