基于J_2项和大气阻力摄动的卫星编队保持方法研究  

The Control Method for Satellites Formation-Keeping Based on J_2 Term Perturbation and Atmosphere Drag

作　　者：刘培玲[1] 周军[1] 刘莹莹[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,西安710072

出　　处：《宇航学报》2010年第5期1357-1361,共5页Journal of Astronautics

基　　金：空间智能控制技术国家级重点实验室基金(SIC07020301)

摘　　要：研究J2摄动和大气阻力对低轨编队卫星相对位置的影响,在此基础上给出一种编队保持方案。文中定量分析了J2摄动对编队卫星三轴相对位置的影响,给出了大气阻力对编队卫星相对轨道要素影响表达式。在同时考虑两种摄动力前提下,推导给出了x方向受摄动的漂移量Δx与编队卫星轨道长半轴之差Δa的周期变化量之间的解析关系式,基于该关系式,设计了单边极限环形式的卫星长期编队保持控制方案。最后通过数学仿真验证了该方案的可靠性,仿真结果与理论分析相符。该控制方案在计算控制量时只需知道编队卫星的轨道长半轴之差,容易实现,为工程实践提供依据。It＇s important to make use of J2 term and atmospheric drag perturbations in low-orbit formation flying,for they are main disturbing forces in those kinds of orbits.Three-axis orbit-drifts caused by J2 term perturbation and differences in classical orbit elements due to atmospheric drag perturbation are concerned in this paper.Considering both J2 term and atmospheric drag Perturbations,an analytic relation between in-track drift Δx and relative semi-major axis perturbation Δa is demonstrated.Based on it,a single side limit cycle control method is designed.The simulation has demonstrated the validity and feasibility of this method.The control period is nearly 2.8 days and Δv is 0.00631 m/s each time.

关 键 词：J2摄动 大气阻力 编队保持 单边极限环 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]