您的位置:首页  > 论文页面

复杂约束下小推力调相轨道精确设计方法

发表时间:2013-06-30  浏览量:1280  下载量:555
全部作者: 尚海滨,王帅
作者单位: 北京理工大学宇航学院
摘 要: 研究了复杂约束下小推力调相轨道精确设计问题。首先,基于改进春分点根数对小推力航天器运动进行了精确建模。然后,对控制律进行了离散化,将离散点的时间以及相应推力方向角作为优化参数,其余时刻的控制律由三次样条插值获得,从而将小推力控制律设计转换为多变量优化问题。为获得全局最优解,采用模拟退火算法与序列二次规划算法进行了全局加局部的优化。以全球定位系统(global positioning system, GPS)卫星、低轨太阳同步卫星和地球同步卫星的调相任务为例进行仿真验证,数值结果表明:该方法可以有效地设计复杂约束下小推力调相轨道。
关 键 词: 航天系统工程;小推力;调相机动;轨道设计;直接法
Title: Precise design of low-thrust phasing orbits with complex constraints
Author: SHANG Haibin, WANG Shuai
Organization: School of Astronautics, Beijing Institute of Technology
Abstract: The precise design problems of low-thrust phasing orbits with complex constraints were studied. Firstly, the motion model of the spacecraft was built based on the modified equinoctial orbital elements. Then, the control law of the low-thrust engine was discretized and the time and the direction angle of the thrust on the pitch points were taken as the optimization parameters.The control law on the other points could be obtained with cubic spline interpolation. Thus, the orbit design was transformed into a multi-parameter optimization problem. Finally, the simulated annealing algorithm and the sequential quadratic programming were employed for solving the optimization problem to get the global optimal solution. The simulation experiments on phasing mission of global positioning system (GPS) satellite, sun synchronous satellite and geostationary satellite showed that the proposed approach can design low-thrust phasing orbits with complex constraints efficiently.
Key words: aerospace system engineering; low-thrust; phasing orbit; orbit design; direct method
发表期数: 2013年6月第12期
引用格式: 尚海滨,王帅. 复杂约束下小推力调相轨道精确设计方法[J]. 中国科技论文在线精品论文,2013,6(12):1170-1176.
 
1 评论数 0
暂无评论
友情链接