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Scilab and Xcos for Very Low Earth Orbits satellites modelling

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Very Low Earth Orbits are orbits in altitudes lower than 450 km. The interaction between the atmosphere particles and the surfaces of the spacecraft is responsible for the aerodynamic torques and forces. Simulating several aspects of the performance of a satellite flying in VLEO is very important to make decisions about the design of the spacecraft and the mission.

Published in: Engineering
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Scilab and Xcos for Very Low Earth Orbits satellites modelling

  1. 1. 1www.esi-group.com Copyright © ESI Group, 2019. All rights reserved.Copyright © ESI Group, 2019. All rights reserved. www.esi-group.com Scilab and Xcos for VLEO satellites modelling David González, Deimos Satellite Systems Scilab Conference 2019
  2. 2. 2www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Discoverer This project has received funding from the European Union’s Horizon 2020 research and innovation programme under grant agreement No 737183. Web page: https://discoverer.space/
  3. 3. 3www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Enabling technologies and developments Discoverer Low drag, atomic oxygen resistant materials Aerodynamic attitude and orbit control Atmosphere breathing electric propulsion Modelling of aerodynamic surfaces Very Low Earth Orbit Satellite Concepts
  4. 4. 4www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. VLEO Benefits • Improved payload performance • Improved launch vehicle payload mass • Reduced space debris collision risk • End-of-life disposal Challenges • Increased atmospheric drag • Increased atomic oxygen erosion • Shorter communications windows with ground stations • Free molecular flow Very Low Earth Orbit O He N2 O2
  5. 5. 5www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Feather and shuttlecock Geometries FeatherShuttlecock
  6. 6. 6www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Xcos model
  7. 7. 7www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Attitude stabilization (Feather) VLEO Orbit: altitude 350km, inclination 50°, agument of perigee 90°, mltan 12h, eccentricity 0.001
  8. 8. 8www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Yaw and pitch Pointing maneuvers (Feather) Accommodation coefficient Settling time (s) Overshoot (%) 0 4281 32.73 0.2 5426 32.86 0.4 9022 33.01 0.6 22513 33.13 0.8 68319 36.06 0.95 - - • Accommodation coefficient (σ)
  9. 9. 9www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Attitude stabilization Shuttlecock
  10. 10. 10www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Feather and shuttlecock comparison Pointing maneuvers Feather Shuttlecock Pointing Angle Settling Time Overshoot(%) Settling Time Overshoot(%) 5 3523 37.8 253 79.3 10 3271 35.7 261 77.8 15 4116 29.5 272 73.7 20 - - 279 69.1 25 - - 312 62.1 30 - - 433 51.5 35 - - 673 42.1 40 - - - -
  11. 11. 11www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Toolbox
  12. 12. 12www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Comparison LEO – VLEO (DTM2013) Toolbox examples
  13. 13. 13www.esi-group.com Copyright © ESI Group, 2019. All rights reserved. Thank you

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