The CanX-7 Drag Sail Mission

Transcription

1 The CanX-7 Drag Sail Mission A cubesat for demonstrating a small-satellite compatible deorbiting device Presented to the 2012 Summer CubeSat Developer s Workshop Jesse Hiemstra, Barbara Shmuel, Fiona Singarayar, Vincent Tarantini, Brad Cotten, Bryan Johnston-Lemke, Grant Bonin, Dr. Robert E. Zee August 2012

2 The Space Debris Problem 2009 Kosmos 2251 & I ridium 33 collision Fengyun-1C antisatellite test Source: Orbital Debris Quarterly News, vol. 361, no. 1802, 15-Jan August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 2

3 Inter-Agency Space Debris Coordination Committee (IADC) Space Debris Mitigation Guidelines (2007) Two protected regions (LEO, GEO). LEO guidelines: deorbit within 25 years from end of mission. Not the law (yet) The Problem for Small Satellites Canadian Department of Foreign Affairs and International Trade (DFAIT), Industry Canada (IC) require debris plan as pre-requisite for communications licenses. Significant issue for Canadian satellites, particularly small, responsive missions. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 3

4 Deorbiting Devices for Small Satellites Propulsion systems (Active) solar sails Electrodynamic tethers Passive drag devices: Ribbons, balloons, sails Image credit: / cmsa.uah.edu/?projects&id= 29 Image credit: / projects/ GOLD/ index.html Image credit: / mission_pages/ smallsats/ nsd_bl uesail.html Image credit: / papers/ TTReno 00.pdf 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 4

5 CanX-7 Mission Objectives Demonstrate a drag sail deorbiting device on a 3U as well as 20 cm edge-length platform, capable of being adapted to passively deorbit a 15 kg reference spacecraft, from an 800 km circular polar orbit, within 25 years. Operate a secondary payload for 6 months, then deploy drag sail. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 5

6 Lifetime Analysis Method What is the deorbit lifetime? Using the Satellite Tool Kit (STK) software lifetime tool, determine the deorbit lifetime of a spacecraft with a fixed drag coefficient and constant ram area. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 6

7 Lifetime Analysis Method De-Orbit Lifetime [years] Selected drag coefficient appears conservative. Drag Coefficient Cd= 2.2 Cd= I nitial Altitude [km] ERS-1 Satellite. ( / ilrs.gsfc.nas a.gov/ satellite_missi ons/ list_of_satellites / ers1_general.html) Solved-for drag coefficients of ERS1, STELLA, and STARLETTE, around one orbit. (I. K. Harrison and G. G. Swinerd, A free molecule aerodynamic investigation using multiple satellite analysis, Planetary Space Science, vol. 44, no. 2, pp , 1996.) 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 7

8 Lifetime Analysis Method Results using most atmospheric models agree, but 35 De-Orbit Lifetime [years] Atmosphere Model 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 8

9 Lifetime Analysis Method Solar activity affects atmospheric density, and solar cycle variation is difficult to predict. Frequency of Occurrence Predicted Lifetime [Years] 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 9

10 Lifetime Analysis Method Deployment date affects deorbit life. De-Orbit Lifetime [years] Starting Altitude 800km 700km 600km 500km Deployment Year 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 10

11 Lifetime Analysis Results Effective ram area requirement is set at 2.0 m year maximum allowable deorbit time Lifetime [Years] 10 1 Starting Altitude 800km 700km 600km Selected minimum effective area requirement Effective Drag Area [m2] 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 11

12 Attitude Analysis Method What size of sail is needed to achieve a given effective area? Conversely, what is the effective area of a given spacecraft and sail? 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 12

13 Attitude Analysis Method Furthermore, the deorbit device must work over a range of orbits and spacecraft configurations. I nclination restricted to (i.e., polar / sunsynchronous). Local Time of Ascending Node (LTAN) free. Altitude free. Magnetic dipole moment restricted. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 13

14 Attitude Analysis Method Parametric Study: Simulate the attitude dynamics, while Holding altitude constant Varying other orbital parameters Varying the atmospheric density through a range equivalent to one solar cycle Varying the magnetic configuration (dipole moment magnitude and direction) Then determine the resulting effective area. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 14

15 Input: Disturbance torques Preliminary Attitude Analysis Results (example) Result: Figures of merit Normalized Aerodynamic Alignment Aerodynamically stabilized Output: Spacecraft attitude Normalized Projected Area Large projected area 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 15

16 Input: Disturbance torques Preliminary Attitude Analysis Results (example) Result: Figures of merit Normalized Magnetic Alignment Magnetically stabilized Output: Spacecraft attitude Normalized Projected Area Low projected area 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 16

17 Input: Disturbance torques Preliminary Attitude Analysis Results (example) Result: Figures of merit Normalized Sunward Alignment Solar radiation pressure stabilized Output: Spacecraft attitude Normalized Projected Area Low projected area 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 17

18 Preliminary Deorbit Analysis Results Figure of Merit: Effective Area Specifically: Dwell-timeweighted average settled projected area, throughout the atmospheric density range equivalent to a whole solar cycle 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 18

19 Preliminary Deorbit Analysis Results Figure of Merit: Effective Area Specifically: Dwell-timeweighted average settled projected area, throughout the atmospheric density range equivalent to a whole solar cycle 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 19

20 Preliminary Deorbit Analysis Results Sail area requirement set at 4.0 m 2 to achieve 2.0 m 2 effective area for most 800 km starting orbits. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 20

21 CanX-7 Spacecraft 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 21

22 Basic Spacecraft Functional Requirements Accommodate primary payload: Deorbit system. Conform to limitations imposed on sail area, magnetic dipole moment, etc. determined from deorbit analysis. Accommodate secondary payload, including specific provisions for attitude control. Survive and operate in the space environment (leads to power, communications, command & data handling, and thermal requirements). 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 22

23 CanX-7 Spacecraft 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 23

24 CanX-7 Spacecraft 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 24

25 Secondary Payload COM DEV Automatic Dependent Surveillance Broadcast (ADS-B) receiver ADS-B GPS position broadcasts are more accurate than radar. Widespread adoption by August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 25

26 Secondary Payload Like radar, ADS-B range is limited by lineof sight. Orbital receivers can enable tracking of aircraft over oceans, eliminating the need for slotting aircraft into routes along waypoints. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 26

27 Attitude Control System Magnetorquer (3 plcs.) 3-Axis magnetometer Solar cell pairs (typ.) used as coarse sun sensor 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 27

28 Communications System S-Band downlink transmitter UHF uplink receiver S-band patch antenna (2 plcs.) UHF monopole antenna (4 plcs.) 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 28

29 Command and Data Handling System Housekeeping computer 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 29

30 Power System Solar cell pairs (Typ.) Battery and regulator Power system electronics 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 30

31 W Throughput Deployed on Canadian Space Agency s Mars Exploration Science terrestrial rover (MESR). Planned for use on NEMO-HD microsatellite First planned spaceflight will be on CanX-7 Modular Power System 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 31

32 Modular Power System For a new spacecraft design Select power system components as needed. Test in-development hardware (payloads, new systems) using already-built power system components. Construct a power system from existing designs and hardware, with less custom hardware. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 32

33 System Architecture Solar Panels I V Modular Power System Blocking Diodes Switches Regulator Loads CanX-7 Hardware Solar Panels Battery and Regulator Switch Card Switch Card Backplane Interface Card Communication and Computing Systems Loads Stock Units Solar Array Filter Batteries and Regulators Switch Cards Backplanes 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 33

34 Deorbit System Drag Sail Module (4 plcs.) 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 34

35 Deorbit System Drag Sail Module (4 plcs.) 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 35

36 Deorbit System Functional Requirements Compatible with 3U and Space Flight Laboratory s (UTIAS-SFL) Generic Nanosatellite Bus (GNB) spacecraft Modular, bolt-on solution Scalable by the addition of modules Capable of repeated deployment (for testing) 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 36

37 Removable sail cartridge Sail Overview Coiled booms: Deployment driven by stored mechanical energy. Sail: ~ 1.0 m 2 per segment. 12 micron doubleside-aluminized Kapton 50-HN. Commercial-off-theshelf (COTS) tape spring booms. 1.4 m long. Spring-loaded door releases to trigger deployment. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 37

38 CanX-7 (3U Bus) Mounting Sail Mounting 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 38

39 Sail Mounting Example of Generic Nanosatellite Bus (GNB) Spacecraft: BRITE Mission 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 39

40 Sail Mounting Conceptual mounting on Generic Nanosatellite Bus (GNB): 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 40

41 Sail Mounting Conceptual mounting options on Nanosatellite for Earth Observation and Monitoring (NEMO) bus: 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 41

42 Preliminary Design Mechanical Design 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 42

43 Third Generation Prototype Mechanical Design 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 43

44 Mechanical Design Prototype Deployment Testing 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 44

45 Mechanical Design Prototype Deployment Testing 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 45

46 CanX-7 Review Modular deorbit device Currently in detailed design phase. ADS-B secondary payload Potentially one of the first demonstrations on-orbit. Modular power system First planned spaceflight for this new system. 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 46

47 Acknowledgements and Questions 20 August 2012 Canadian Advanced Nanospace experiment 7 - CanX-7 47

48 20 August