Orbital rendezvous using two-step sliding mode control |
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| Institution: | 1. Korea Astronomy Observatory, Applied Astronomy Division / GPS Team, San 36-1, Whaam-dong, Yusong-ku, Taejon, 305-348, South Korea;2. Department of Astronomy, Yonsei University, Seoul, 120-749, South Korea;3. Radio & Broadcasting Technology Laboratory, Electronics and Telecommunications Research Institute, Yusong P.O. Box 106, Taejon, 305-600, South Korea;1. School of Astronomy and Space Science, Nanjing University, Nanjing 210093, China;2. Satellite Communication and Navigation Collaborative Innovation Center, Nanjing 210007, China;1. School of Astronautics, Beihang University, Beijing 100191, China;2. Beijing Institute of Spacecraft System Engineering, Beijing 100094, China |
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| Abstract: | The problem of spacecraft rendezvous is studied, using sliding mode control in the presence of the earth's gravitational perturbation. The impulsive solution of Lambert's problem is obtained using the combined equations method to minimize total ΔV via an iterative method, and it is used as the desired trajectory for the rendezvous. In this paper, a two-step sliding mode control method is introduced for solving the rendezvous problem with finite-thrust including unmodeled dynamics.The thrust-coast-thrust type control laws for the system to follow the desired trajectories are represented and resultant trajectories are close enough to the Lambert's orbit with comparable amount of ΔV to the Lambert's impulsive solution. All state variables matched the final boundary conditions reasonably well at the end of maneuver. |
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