椭圆轨道编队飞行相对动力学初始化条件

Hill方程在椭圆轨道编队设计中具有一定的局限性,为解决这一问题,将基于Hill方程的圆轨道编队设计方法推广应用于椭圆轨道编队设计中．将T-H方程表示为参考轨道真近点角的显函数形式,推导椭圆轨道编队相对运动的状态转移矩阵．利用椭圆轨道编队相对运动动力学方程有周期解的要求,讨论椭圆轨道编队周期性运动的一般性初始化条件．最后通过数学仿真表明理论推导的正确性．推导的初始化条件可用于椭圆轨道编队队形初始设计或相对运动误差估计．

Relative dynamics and initialization condition for formation flying in elliptical orbits

Hill equations have definite limitation in the design of satellite formation flying in elliptical orbits, to solve this problem,the design method of satellite formation flying in circular orbits based on Hill equation can be generalize and applied to the formation flying in elliptical orbits.T - H equation is expressed as the ex- plicit function form of reference orbit true anomaly,and the state transition matrix of relative motion of satellite formation flying in elliptical orbits is derived.According to the requirement that relative dynamics equation of satellite formation flying in elliptical orbits has periodicity solution,the general initialization condition of perio- dicity motion that satellite formation flying in elliptical orbits is discussed.Finally,based on the theoretical re- suits,some numerical simulations are carried out.The initialization condition derived can be applying in initial design of formation flying in elliptical orbits or relative motion error estimation.