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Optimal approach to halo orbit control

Rahmani, A ; Sharif University of Technology | 2003

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  1. Type of Document: Article
  2. DOI: 10.2514/6.2003-5748
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2003
  4. Abstract:
  5. Three-dimensional orbits in the vicinity of the collinear libration points of the Sun-Earth/Moon barycenter system are currently being considered for use with a number of missions planed for 2000 and beyond. Since such libration point trajectories are, in general, unstable, spacecraft moving on these paths must use some form of trajectory control to remain close to their nominal orbit. In this paper, circular restricted three body problem is reviewed and a numerical method to control spacecrafts on periodic halo orbits around L1 and L2 collinear points of the Sun-Earth/Moon barycenter system is investigated. The control approach is based on the optimal control theory and implements variation of extremals technique to solve the resulting two point boundary value problem. The reference trajectory, halo orbit, is supposed to be given in the form of the Fourier series. © 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved
  6. Keywords:
  7. Boundary value problems ; Space flight ; Orbital transfer ; Numerical methods ; Fourier series
  8. Source: AIAA Guidance, Navigation, and Control Conference and Exhibit 2003, Austin, TX, 11 August 2003 through 14 August 2003 ; 2003 ; 9781563479786 (ISBN); 9781624100901 (ISBN)
  9. URL: https://arc.aiaa.org/doi/10.2514/6.2003-5748