基于迹向控制量的编队星群相位控制

摘要/Abstract

摘要： 为了得到控制量与控制时机对相位改变的直观公式，基于Hill方程以及迹向控制的约束条件，定性分析共面绕飞编队中控制量、控制时机与编队卫星相位之间的关系，分析结果表明：当需要改变的相位角小于90°时，可实现最省燃料的控制；当需要改变的相位角大于90°时，可进行趋于最小控制量的控制；当在相对运动椭圆上下点实施控制时，相位无变化.

关键词: Hill方程, 迹向机动, 相位控制

Abstract: In terms of the engineering constraints, orbital maneuvering along the track is relatively easy to achieve. The relations among the quantity of control, the time of control and the phase are studied，that are based on the constrains of Hill equations and the alongtrack control for the coplanar flying-around formation. The analytical results demonstrate that the minimum fuel consumption can be realized when the phase angle needing to change is less than 90°. Conversely, the minimum quantity of control can be approached when the phase angle needing to change is larger than 90°. And further, it is found that the phase remains unchanged when the control is carried out at the up and down points of the relative motion ellipse.

Key words: Hill equations, track maneuvering, phase control

吴会英, 周美江, 齐金玲. 基于迹向控制量的编队星群相位控制[J]. 空间控制技术与应用, 2014, 40(6): 31-35.

WU Hui-Ying, ZHOU Mei-Jiang, QI Jin-Ling. Formation Phase Control Based on the along-Track Control Strategy[J]. , 2014, 40(6): 31-35.

参考文献

1］郗晓宁，王威，高玉东.近地航天器轨道基础［M］.长沙：国防科技大学出版社，2003：244247. XI X N, WANG W, GAO Y D. Fundamentals of nearearth spacecraft orbit ［M］. Changsha : Nation University of Defense Technology Press, 2003：244247. ［2］文援兰，宋以胜，文景.共面编队飞行卫星星座的控制［J］.国防科技大学学报，2004，26(3)：2428. WEN Y L, SONG Y S,WEN J. The control of the satellites coplanar formation flying ［J］. Journal of National University of Defense Technology, 2004, 26(3)：2428. ［3］黄美丽，向开恒.编队飞行卫星群相对轨道摄动运动分析［J］. 中国空间科学技术，2006，26(6)：1319. HUANG M L, XIANG K H. Perturbation analysis of the relative orbits of formation flying satellite ［J］. Chinese Space Science and Technology, 2006,26(6)：1319. ［4］师鹏,李保军,赵育善.有限推力下的航天器绕飞轨道保持与控制［J］. 北京航空航天大学学报，2007，33(7)：757760. SHI P, LI B J,ZHAO Y S. Orbital maintenance and control of spacecraft flyaround with finitethrust ［J］. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(7)：757760. ［5］杨维廉.基于轨道摄动解的卫星编队飞行［J］. 宇航学报，2008，29(4)：11661171. YANG W L. Formation flying based on orbit perturbation solution ［J］. Journal of Astronautics, 2008, 29(4)：11661171. ［6］吴会英，陈宏宇，余勇，等.远距离轨道接近及绕飞控制技术研究［J］.中国空间科学技术，2010，30(1)：2533. WU H Y, CHEN H Y, YU Y，et al. Study of longdistance approaching and companion flying technology ［J］. Chinese Space Science and Technology, 2010, 30(1)：2533. ［7］吴会英，陈宏宇，周美江，等.伴随卫星轨控时机与相对运动椭圆大小控制效率的关系［J］. 载人航天，2013，19(5)：9096. WU H Y, CHEN H Y, ZHOU M J，et al. Research on relation between orbit control time and control efficiency of company satellites ［J］. Manned Spaceflight, 2013, 19(5)：9096.