基于轨道动力学的椭圆轨道悬停方法  

An Orbit Dynamics-Based Elliptical Orbit Hovering Method

作　　者：王功波[1] 孟云鹤[1] 郑伟[1] 汤国建[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《宇航学报》2010年第6期1527-1532,共6页Journal of Astronautics

基　　金：国家自然科学基金(10702078)

摘　　要：连续有限推力条件下,基于动力学原理设计了伴随卫星相对于椭圆轨道的参考卫星在任意位置实现悬停的方法。给出了对任意椭圆参考轨道实现悬停的开环控制律,推导了一个周期内的速度增量计算公式。特别分析了参考卫星为"Molniya"轨道时,实现悬停需要的控制推力及速度增量。仿真结果表明,"Molniya"轨道正下方1km的悬停伴飞,一个轨道周期时间内连续有限推力发动机需要产生的速度增量为10.317m/s。文章提出的方法也可用于椭圆轨道的空间圆或水平圆等非自然编队构型设计。Given that the satellite＇s engine could provide a continuous finite thrust,a hovering method at any selected position in elliptical orbit is presented based on dynamics theory in this paper.An open loop orbit control strategy to maintain hovering is proposed,and the velocity increment required during a orbit period is derived.Example is given especially when the reference orbit is a typical kind of ＂Molniya＂ elliptical orbit.Simulation results show that for the hovering right below the＂Molniya＂satellite with the distance of 1 km,the velocity increment required in a orbit period is 10.317 m/s.The method presented in this paper can also be used to design elliptical Non-Keplerian formations such as space circle and horizontal circle.

关 键 词：连续有限推力 轨道动力学 椭圆轨道 悬停轨道 速度增量 

分 类 号：V448[航空宇航科学与技术—飞行器设计]