| 椭圆轨道编队的构形变化控制方法 |
| |
| 引用本文： | 于萍,张洪华.椭圆轨道编队的构形变化控制方法[J].中国空间科学技术,2006,26(1):1-8. |
| |
| 作者姓名： | 于萍 张洪华 |
| |
| 作者单位： | 北京控制工程研究所,北京,100080 |
| |
| 摘 要： | 推导了椭圆轨道编队的一些典型构形模态,指出椭圆轨道卫星编队的模态不同于圆轨道的构形模态,是极为丰富的。基于T-H方程的解析解,推导了副星在沿航向常值推力作用下的椭圆轨道编队的构形变化控制方法。推导的构形变化控制方法,通过合理的选择控制量的作用时刻,可达到大量节约燃料的目的。最后,给出仿真算例。
|
| 关 键 词： | 编队飞行 椭圆轨道 控制 |
| 收稿时间： | 2005-01-17 |
| 修稿时间： | 2005-02-28 |
Formation Control for Spacecraft in Eccentric Orbits |
| |
| Yu Ping,Zhang Honghua.Formation Control for Spacecraft in Eccentric Orbits[J].Chinese Space Science and Technology,2006,26(1):1-8. |
| |
| Authors: | Yu Ping Zhang Honghua |
| |
| Institution: | Beijing Institute of Control Engineering, Beijing 100080 |
| |
| Abstract: | Some formation modes of spacecraft formation flying in eccentric orbits are derived.The formation modes in eccentric orbits are more than the formation modes in circular orbits.Based on the Tschauner-Hempel equation the formation control algorithm for spacecraft in eccentric orbits is put forward.The control acceleration is on the track of orbit and is fixed in this control(algorithm).The control schedule is optimized in order to economize fuel.Furthermore,numerical(examples) and simulation results are also given to verify the effectiveness of the algorithms proposed above. |
| |
| Keywords: | Formation flight Elliptical orbit Control |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
|
