| 三维电动力绳系子卫星轨道转移的最优控制 |
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| 引用本文： | 刘丽丽,文浩,金栋平,胡海岩.三维电动力绳系子卫星轨道转移的最优控制[J].计算力学学报,2011,28(2):178-182. |
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| 作者姓名： | 刘丽丽 文浩 金栋平 胡海岩 |
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| 作者单位： | 1. 南京航空航天大学振动工程研究所飞行器结构力学与控制教育部重点实验室,南京210016;中南大学土木建筑学院力学系,长沙410075
2. 南京航空航天大学振动工程研究所飞行器结构力学与控制教育部重点实验室,南京,210016 |
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| 基金项目： | 国家自然科学基金(10902127,10672073);中南大学前沿研究计划(2010QZLJ002)部分资助项目. |
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| 摘 要： | 考虑复杂状态和控制约束的作用,研究了倾斜轨道上三维电动力绳系子卫星轨道转移的最优控制问题.借助Gauss伪谱算法,将绳系子卫星轨道转移的连续时间最优控制问题离散为大规模动态规划问题,并利用非线性规划方法进行求解.通过数值仿真计算了最优控制时间、子星最优转移轨道及最优控制张力和电流,同时讨论了轨道倾角对最优控制量的影响....
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| 关 键 词： | 电动力绳系卫星 最优控制 轨道转移 非线性规划 |
| 收稿时间： | 2009/5/11 0:00:00 |
| 修稿时间： | 2010/12/30 0:00:00 |
Three-dimensional optimal control of orbit transfer for an electrodynamic tethered subsatellite |
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| LIU Li-li,WEN Hao,JIN Dong-ping and HU Hai-yan.Three-dimensional optimal control of orbit transfer for an electrodynamic tethered subsatellite[J].Chinese Journal of Computational Mechanics,2011,28(2):178-182. |
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| Authors: | LIU Li-li WEN Hao JIN Dong-ping and HU Hai-yan |
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| Institution: | Institute of Vibration Engineering Research, MOE Key Lab of Structure Mechanics and Control for Aircraft, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;School of Civil Engineering and Architecture, Central South University, Cha;Institute of Vibration Engineering Research, MOE Key Lab of Structure Mechanics and Control for Aircraft, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Institute of Vibration Engineering Research, MOE Key Lab of Structure Mechanics and Control for Aircraft, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Institute of Vibration Engineering Research, MOE Key Lab of Structure Mechanics and Control for Aircraft, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | A nonlinear optimal control scheme is presented for solving the orbit transfer problem of a tethered subsatellite system on an inclined orbit. The scheme accounts for the three-dimensional motions of the system as well as the complex state-control constraints. The nonlinear optimal control problem is solved by discretizing it first, based on the Gauss pseudospectral method, and then solving the resulting large-scale optimization problem via nonlinear programming. The presented scheme is used to find the optimal solutions for the transfer time, the system states, the tensional force and the electric current, and the effects of orbit inclination on the optimal solutions are also evaluated through a summary discussion. It is demonstrated through the case studies that the subsatellite can be maneuvered, under the mission-related constraints, from a nominal equilibrium position (below the mother satellite) to another equilibrium one (above the mother satellite) by changing only the tensional force and the electric current. |
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| Keywords: | electrodynamic tethered subsatellite optimal control orbit transfer nonlinear programming |
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