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Optimal control of the deployment process of solar wings on spacecraft
Institution:1. Basic Science Courses Department, Beijing Institute of Machinery, Beijing 100085, China;2. Department of Mechanics, Shanghai Institute of Applied Mathematics and Mechanics, Shanghai University, Shanghai 200072, China;3. Department of Engineering Mechanics, Shanghai Jiao Tong University, Shanghai 200030, China;1. Department of Chemical Engineering, National Taiwan University, Taipei, Taiwan;2. Graduate Institute of Applied Science & Technology, National Taiwan University of Science and Technology, Taipei, Taiwan;3. Department of Chemical Engineering, National Taiwan University of Science and Technology, Taipei, Taiwan;4. Key Laboratory of Low-Grade Energy Utilization Technologies and Systems, Chongqing University, Chongqing 400030, China;5. Institute of Engineering Thermophysics, Chongqing University, Chongqing 400030, China;1. Department of Engineering Mechanics, Northwestern Polytechnical University, Xi''an 710129, PR China;2. Department of Mechanics, Key Lab of Fluid Power Transmission and Control, Zhejiang University, Hangzhou 310027, PR China;1. Sustainable Environment Research Centre (SERC), Faculty of Advanced Technology, University of Glamorgan, Pontypridd, Mid-Glamorgan CF37 1DL, UK;2. Sustainable Environment Research Centre (SERC), Faculty of Health, Sport and Science, University of Glamorgan, Pontypridd, Mid-Glamorgan CF37 1DL, UK;1. Robots & Intelligent Systems Lab, Gyeongsang National University, Jinju, Republic of Korea;2. School of Mechanical and Aerospace Engineering & ReCAPT, Gyeongsang National University, Jinju, Republic of Korea
Abstract:The optimal attitude control problem of spacecraft during the stretching process of solar wings is investigated in this paper. The dynamical equations of the nonholonomic system are derived from the conservation principle of the angular momentum of the multibody system. Attitude control of the spacecraft with internal motion is reduced to a nonholonomic motion planning problem. The spacecraft attitude control is transformed into the steering problem for a drift free control system. The optimal solution for steering a spacecraft with solar wings is presented. The controlled motion of spacecraft is simulated for two cases. The numerical results demonstrate the effectiveness of the optimal control approach.
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