摘要
Hill方程和Clohessy-Wiltshire方程广泛用于解决编队飞行卫星的相对运动,这些方程的线性化基于三点假设:理想球体、圆参考轨道和相对距离足够近。这些假设带来较大的模型误差,没有考虑J2摄动的影响和椭圆参考轨道。针对这个问题,提出一种线性化的相对运动模型,充分考虑了J2摄动带来的相对运动长期漂移,以及利用J2摄动下瞬根与平根的转化,建立了基于初始瞬根和瞬根差的椭圆参考轨道相对运动模型。仿真结果表明该模型有效。
The most widely used relative motion model of satellite formation Flying is the Hill＇s equation and Clohessy-Wiltshire＇s（C.W＇s） equations.The linearized equations are based on three hypothesis： ideal sphere circular reference orbit and relative distance being close enough.The hypothesis brings model error that J2 Perturbation and elliptical reference Orbit isn＇t taken into accounted.A linearized relative motion model was addressed.Considering the impact of the J2 Perturbation on Secular drift of relative motion,mean orbit elements and instant orbit elements,relative motion model of elliptical reference orbit was developed based on initial instant orbit elements and its drift.Result of simulations demonstrates the efficacy of the model.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2011年第4期648-651,共4页
Journal of System Simulation
基金
基于编队卫星的测控管理技术研究(装字第1639号)
关键词
编队飞行
椭圆参考轨道
相对运动
轨道根数
formation flying
elliptical reference orbit
relative motion
orbit elements
