近圆轨道航天器伴随飞行控制方法研究  

Control Strategy Study of Spacecraft Adjoint Flying in Near Circular Orbit

作　　者：郭碧波[1] 强文义[1] 梁斌[1] 李成[1] 

机构地区：[1]哈尔滨工业大学空间智能系统研究所,哈尔滨150001

出　　处：《宇航学报》2008年第6期1871-1877,共7页Journal of Astronautics

基　　金：国家863计划资助项目(2005AA745060)

摘　　要：对近圆轨道上航天器在轨长期伴随飞行的轨道控制方法进行了研究。比较了采用C-W方程(Clohess-Wiltsire)解析解和轨道根数两种方法描述相对运动的相同点和差异。分析影响航天器长期伴随飞行的各种因素。在总结相对运动规律的情况下设计轨道修正条件,提出两种伴随飞行的轨道控制方法,并分别对两种方法的控制效果进行理论分析。数学仿真结果表明两种控制方法都能实现航天器长期伴随飞行,且第二种方法能够较大程度上节省燃料消耗。This paper studied the orbital control strategy of spacecraft long-time adjoint flying in near circular orbit. Two depictions of relative motion based on Clohessy-Wihsire （C-W） equations and orbit elements were compared. Then the factors which effected spacecrafts long-time adjoint flying were listed and analyzed. After summarizing relative motion, an orbit modulation condition was designed. Following that, two orbital control strategies of adjoint flying were proposed, and the control effects were evaluated theoretically. Numerical simulation shows that two strategies can actualize spacecrafts＇ long-time adjoint flying, and the second one realizes it with less fuel by a large extent.

关 键 词：近圆轨道 伴随飞行 相对运动 轨道修正 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]