Impulsive control for angular momentum management of tumbling spacecraft |
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| Institution: | 1. Advanced Technology R&D Center, Mitsubishi Electric Corporation, Japan;2. Graduate School of Engineering, Nagoya University, Japan;1. Mechanical, Aerospace, and Nuclear Engineering Department, Rensselaer Polytechnic Institute, 110 8th street, Troy, NY 12180, USA;2. Research Aerospace Engineer, Air Force Research Laboratory, Space Vehicles Directorate, Kirtland AFB, NM, USA;1. Research Center for Intelligent Robotics, School of Astronautics, Northwestern Polytechnical University, Xi’an, Shaanxi, 710072, China;2. National Key Laboratory of Aerospace Flight Dynamics, Northwestern Polytechnical University, Xi’an, Shaanxi, 710072, China;1. Shanghai Engineering Center for Microsatellites, Shanghai 201203, China;2. Key Lab of Microsatellite, Chinese Academy of Sciences, Shanghai 201203, China;3. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;1. Science and Technology on Space Intelligent Control Laboratory, 100190 Beijing, PR China;2. Beijing Institute of Control Engineering, 100190 Beijing, PR China;1. Department of Aerospace Engineering, Sharif University of Technology, Tehran, 14588-89694, Iran;2. Center for Research and Development in Space Science and Technology, Sharif University of Technology, Tehran, 14588-89694, Iran |
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| Abstract: | We discuss an angular momentum control of a tumbling spacecraft. The proposed control method is to apply an impulse by a space robot arm, to measure and control the relative position and attitude between the target spacecraft, and then to apply another impulse until the rotational motion of the target spacecraft is well damped. A discrete controller is designed using the simplified equations of rotational motion through appropriate coordinate transformation. The stationary response under contact model uncertainty is investigated and stability condition is analytically derived. Numerical simulations are given to validate the proposed approach. |
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