卫星编队飞行中C-W方程与轨道根数法的比较  

Comparison of Two Methods in Satellite Formation Flying

作　　者：高云峰[1] 宝音贺西[1] 李俊峰[1] 

机构地区：[1]清华大学工程力学系,北京100084

出　　处：《应用数学和力学》2003年第8期799-804,共6页Applied Mathematics and Mechanics

基　　金：国家自然科学基金资助项目(10202008);中国博士后基金资助项目((2001)31)

摘　　要：　目前卫星编队飞行动力学与控制的研究得到了广泛的重视,这些研究的理论主要是基于描述卫星相对运动的Clohessy＿Wiltshire(C＿W)方程·　但根据特例及定性分析,表明C＿W方程在初始条件的选取、解的周期性等方面与实际情况不符,从星的能量也不守恒·　以卫星轨道根数为基础,提出了卫星编队飞行中的相对轨道根数法,克服了C＿W方程的局限性,物理概念清楚,应用范围广,解的周期性成为自然结论·　在主星为小偏心率的情况下,得到了简化的相对运动方程·　最后对两种方法进行了比较。Recently, the research of dynamics and control of the satellite formation flying has been attracting a great deal of attentions of the researchers. The theory of the research was mainly based on Clohessy-Wiltshire' s (C-W's) equations, which describe the relative motion between two satellites. But according to some special examples and qualitative analysis , neither the initial parameters nor the period of the solution of C-W' s equations accord with the actual situation, and the conservation of energy is no longer held. A new method developed from orbital element description of single satellite , named relative orbital element method ( ROEM) , was introduced. This new method, with clear physics conception and wide application range, overcomes the limitation of C-W s equation , and the periodic solution is a natural conclusion. The simplified equation of the relative motion is obtained when the eccentricity of the main satellite is small. Finally, the results of the two methods (C-W' s equation and ROEM) are compared and the limitations of C-W s equations are pointed out and explained.

关 键 词：卫星编队飞行 相对运动 C-W方程 相对轨道根数 周期解 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]