在轨释放伴随卫星方法与仿真分析  

Simulation and Analysis of On-orbit Release of Companion Satellite

作　　者：杜新明[1,2] 高慧婷[2] 杨新[2] 

机构地区：[1]中国科学院研究生院,北京100049 [2]中国科学院光电研究院,北京100190

出　　处：《计算机仿真》2009年第10期39-42,76,共5页Computer Simulation

摘　　要：伴随卫星的轨道动力学分析与仿真是航天器伴随领域的一个重要研究方向。为飞行器执行警卫任务,以动力学方法为基础,建立了卫星的绝对轨道模型和伴飞轨道维持模型,推导了简化的相对运动方程解析解,并作为对伴星进行轨道维持的依据。仿真分析不同释放方案形成的共面椭圆伴飞轨道,伴星的燃料消耗,轨道维持措施对伴飞的影响。仿真结果表明,伴星活动范围越大,轨道维持所耗燃料越多;增加轨道维持措施可延长伴飞圈数;在满足应用任务要求的前提下,选定合适的伴星释放方案,能够实现燃料消耗最少。The orbital dynamic analysis and simulation is an important research direction in the field of spacecraft adjoint motion. The paper builds up an orbit model and an orbital - keeping model based on the kinetic methods, deduces the analytical solutions of simplified relative motion equations of companion satellite. Research contents inelude ： the eoplanar elliptical adjoint orbits based on different orbital transfer schemes, the fuel consumption of differ- ent phases and the effec of control measures in keeping phase. The results show that the larger the range of adjoint motion is, the more fuel used; the number of flight circles can be increased by orbital keeping; under the premise of meeting a certain application task requirements, the second orbital transfer scheme proves to be stable and energy saving.

关 键 词：伴随卫星 伴飞轨道 燃料消耗 轨道维持 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]