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Spacecraft Formation Flying near Sun-Earth L2 Lagrange Point: Trajectory Generation and Adaptive Full-State Feedback ControlIn this paper, we present a method for trajectory generation and adaptive full-state feedback control to facilitate spacecraft formation flying near the Sun-Earth L2 Lagrange point. Specifically, the dynamics of a spacecraft in the neighborhood of a Halo orbit reveals that there exist quasi-periodic orbits surrounding the Halo orbit. Thus, a spacecraft formation is created by placing a leader spacecraft on a desired Halo orbit and placing follower spacecraft on desired quasi-periodic orbits. To produce a formation maintenance controller, we first develop the nonlinear dynamics of a follower spacecraft relative to the leader spacecraft. We assume that the leader spacecraft is on a desired Halo orbit trajectory and the follower spacecraft is to track a desired quasi-periodic orbit surrounding the Halo orbit. Then, we design an adaptive, full-state feedback position tracking controller for the follower spacecraft providing an adaptive compensation for the unknown mass of the follower spacecraft. The proposed control law is simulated for the case of the leader and follower spacecraft pair and is shown to yield global, asymptotic convergence of the relative position tracking errors.
Document ID
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Wong, Hong
(Polytechnic Univ. Brooklyn, NY, United States)
Kapila, Vikram
(Polytechnic Univ. Brooklyn, NY, United States)
Date Acquired
August 23, 2013
Publication Date
September 1, 2004
Publication Information
Publication: Proceedings from the 2nd International Symposium on Formation Flying Missions and Technologies
Subject Category
Spacecraft Design, Testing And Performance
Funding Number(s)
Distribution Limits
Public Use Permitted.
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