利用参照轨道要素设计卫星编队轨道  

ORBIT DESIGN FOR SATELLITES IN FORMATION FLIGHT USING REFERENCE ORBITAL ELEMENTS

作　　者：王虎妹[1] 李俊峰[1] 杨卫[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《工程力学》2006年第4期144-148,154,共6页Engineering Mechanics

基　　金：高等学校博士学科点专项科研资助课题基金资助项目(20020003024)

摘　　要：利用球面几何方法,引入参照轨道要素概念,给出其定义,并推导了用其描述的从星相对运动方程的精确形式。在主星偏心率为零时,根据编队飞行中相对轨道倾角很小的特点,对相对运动方程进行简化并分析相对运动的特征。设计了由一颗主星和六颗从星构成合成孔径静止侦察卫星的编队应用,给出编队队形特征和主星的轨道参数,从相对运动方程计算出编队中的六颗从星的轨道要素。数值仿真结果表明:简化的方程具有很高的精度,对编队队形设计问题完全适用。The concept and the definition of the reference orbital elements are introduced using spherical geometry. In terms of the reference orbital elements, governing equations for relative motion are formulated. Under the assumption of null eccentricity of the leader satellite, as well as the small relative inclination angle in formation flight, the equations of relative motion are simplified considerably and the characteristics of relative motion are extracted. The utility of the present formulation is exemplified by constructing the formation flight of one leader and six follower satellites, which carry the synthetic-aperture reconnaissance mission in the geosynchronous orbit. The formation parameters and the orbital elements of the leader satellite are obtained to meet the application demands. The orbital elements of six follower satellites are also identified using the relative motion equations. The simulation results show that simplified equations are reasonably accurate and are suitable for orbit design of formation flight.

关 键 词：航天器飞行力学 卫星编队飞行 相对轨道 轨道要素 参照轨道要素 

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]