Attitude control of a satellite with redundant thrusters |
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| Institution: | 1. School of Mechanical and Aerospace Engineering, Sunchon National University, 315 Maegok-dong, Suncheon, Jeonnam 540-742, Korea;2. Korea Aerospace Research Institute, P.O. Box 113, Eoeun-Dong, Yuseong-Gu, Daejeon 305-601, Korea;3. Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology, 373-1, Kuseong-Dong, Yuseong-Gu, Daejeon 305-701, Korea;1. Department of Control Engineering, Faculty of Electrical Engineering, South Tehran Branch, Islamic Azad University (IAU), No. 209, North Iranshahr St., PO Box 11365/4435, Tehran, Iran;2. Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran;3. Department of Control Engineering, Khajeh Nasir Toosi University of Technology, Tehran, Iran;1. School of Automation Science and Electrical Engineering, Beihang University, Beijing, China;2. Advanced Innovation Center for Big Data-Based Precision Medicine, Beihang University, Beijing, China;3. Systems Engineering Research Institute, China State Shipbuilding Corporation, Beijing, China;4. The 9th Designing of China Aerospace Science and Industry Corporation, Wuhan, China;1. E-USOC, Center for Computational Simulation, Escuela Técnica Superior de Ingeniería Aeronáutica y del Espacio, Universidad Politécnica de Madrid, Plaza de Cardenal Cisneros 3, 28040 Madrid, Spain;2. Altran, Aerospace & Defense Division, Systems Engineering Department, 1st Campezo st, 28022 Madrid, Spain |
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| Abstract: | Redundant thrusters are generally used for a reliable attitude control system. Also, redundant thrusters yield a better performance if they are used appropriately. In this paper, the authors propose an efficient redundancy management algorithm to reduce the fuel consumption. The algorithm is based on a linear programming problem which is a constrained optimization problem. For the algorithm, a cost function is defined as a quantity related to the fuel consumption for a maneuver. The independent variables are the thrusters' on-times which are control input variables of a satellite dynamic model. The advantage of the proposed method is verified by numerical examples. The examples show that the proposed method consumes less fuel than an existing method for a given maneuvering command. A sub-optimal algorithm is also discussed for an onboard computation. The proposed algorithm is applied to two maneuvers: move-to-rest and rest-to-rest. This is verified by a numerical simulation. |
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