1 / 29

Maksim Shirobokov Sergey Trofimov Mikhail Ovchinnikov (speaker)

68th International Astronautical Congress Adelaide, Australia, September 25-29, 2017 IAC-17.C1.7.4 Station-Keeping of Sun-Venus L2 Libration Point Orbits for a Prospective Space Observatory Mission. Maksim Shirobokov Sergey Trofimov Mikhail Ovchinnikov (speaker)

Download Presentation

Maksim Shirobokov Sergey Trofimov Mikhail Ovchinnikov (speaker)

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript


  1. 68th International Astronautical CongressAdelaide, Australia, September 25-29, 2017IAC-17.C1.7.4Station-Keepingof Sun-Venus L2 Libration Point Orbits for a Prospective Space Observatory Mission Maksim Shirobokov Sergey Trofimov Mikhail Ovchinnikov (speaker) Keldysh Institute of Applied Mathematics

  2. Contents • Motivation • Dynamics inthe vicinity of L2 • Station-keeping simulation algorithm • Results • Conclusions

  3. Missions to libration point orbits and station-keeping characteristics

  4. Advantages of using the Sun-Venus L2 libration point orbits • Good location for telescopes that observe the hazardous asteroids with the low aphelion • Flexible shadow conditions and absence of Venus in the camera’s field of view • Low station-keeping costs NEO Survey spacecraft Credit: Ball Aerospace & Technologies Corporation

  5. Solar eclipse geometry

  6. Rotating reference frame Mass parameter Non-dimensional units: The Sun-Venus system

  7. Equations of motion in the CR3BP In the rotating frame where Equilibrium points meet conditions and are called the libration points

  8. Lissajous orbit 3,400 x 10,842 x 1,900 km

  9. Mean, minimum and maximum illumination coefficients for different Lissajous orbits

  10. Halo orbit with the y-amplitude of 489,290 km

  11. Family of halo orbits

  12. Evolution of the Floquet diagrams along the family of halo orbits

  13. The station-keeping simulation algorithm • Design the reference orbit in the high-fidelity model of motion and specify the target points at the times , respectively • Simulate the orbit insertion errors where

  14. Two types of the control • The x-axis control: find such that after applying , the objective is minimized • The 3-axis control: find such that after applying the objective is minimized

  15. Navigation errors • Simulate the navigational errors before applying the impulse where

  16. Impulse execution errors • Simulate the impulse execution errors where and the rotational matrix perform a random rotation with the normally distributed cone angle and the uniformly distributed clock angle • If , then the impulse is skipped

  17. Levels of uncertainties • Orbit insetion errors: • Navigation errors: • Impulse execution errors: • Minimum : • Number of points downstream:

  18. Mean annual station-keeping cost, its standard deviation and the maximum deviation from the reference orbit x-axis control 3-axis control

  19. Approximate bounds of the central manifold (CR3BP)

  20. Approximate bounds of the central manifold (Full)

  21. Conclusion • The station-keeping cost for Lissajous orbits with a different mean illumination degree is approximately the same and equals 1.14 m/s • The station-keeping cost for halo orbits is slighly less than for Lissajous orbits and decreases as the amplitude increases • The station-keeping costs for the 3-axis control are by 6-10% larger than for the x-axis control • Required navigational accuracies when targeting the xz-plane are estimated for stable halo orbits

  22. Thank you for your attention! This work is fully supported by the Russian Science Foundation grant 14-11-00621.

  23. Backup

  24. Literature review • D. W. Dunham and A. L. Genova. Using Venus for locating space observatories to discover potentially hazardous asteroids. Cosmic Research, 48(5):424-429, 2010. • K.G. Raikunov. Structure and design of the orbital segment of the Earth's asteroid information system. Ph.D. Thesis, Bauman Moscow State Technical University, 2016 (in Russian). • Yu. S. Bodrova and K.G. Raikunov. Rational variants for deployment of space telescopes for concurrent detection of asteroids. In XLI Academic Readings on Cosmonautics, Moscow, 2017. • R. E. Gold. SHIELD - A Comprehensive Earth Protection System. A Phase I Report to the NASA Institute for Advanced Concepts, 1999. • R. Arentz et al. NEO Survey: An Ecient Search for NearEarth Objects by an IR Observatory in a Venuslike Orbit. In AIP Conference Proceedings, volume 1208, pages 418-429. AIP, 2010. • National Research Council. Defending Planet Earth: Near-Earth-Object Surveys and Hazard Mitigation Strategies. The National Academies Press, Washington, DC, 2010. • R.Z. Akhmetshin. Space based Optical Barrier in the Problem of Asteroid Hazard. Keldysh Institute Preprints, (29):1-32, 2012. • R. Z. Akhmetshin. Space patrol: Variants of the optical barrier scheme. Cosmic Research, 51(4):241-253, 2013. • E. T. Lu, H. Reitsema, J. Troeltzsch, and S. Hubbard. The B612 Foundation Sentinel Space Telescope. New Space, 1(1):42-45, 2013. • D. W. Dunham et al. A Concept for Providing Warning of Earth Impacts by Small Asteroids Solar System Research, 47(4):315-324, 2013.

  25. Equations of motion in the high-fidelity model

  26. Sources of pertubrations

  27. Mean illumination coefficients for different Lissajous orbits

  28. Histogram of the annual station-keeping costs for the 6,050x3,400 km Lissajous orbit; the x-axis control.

  29. Mean annual station-keeping cost, its standard deviation, and the maximum deviation from the reference orbit for different levels of the orbit insertion and navigational uncertainties; the x-axis contol

More Related