考虑太阳引力摄动的Halo轨道保持控制  

Halo orbit station-keeping for in the presence of solar gravitational perturbations

作　　者：车征[1] 李俊峰[1] 宝音贺西[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《清华大学学报（自然科学版）》2009年第2期285-288,共4页Journal of Tsinghua University(Science and Technology)

基　　金：国家自然科学基金资助项目(10672084);博士点基金资助(20060003097)

摘　　要：研究了考虑太阳引力影响的地-月系统中绕L2点轨道的保持问题。在地-月系统圆形限制性三体问题的基础上,考虑太阳的影响,先用微分修正法得到飞行器的初始状态,然后根据方程的对称性,分别沿时间的负向、正向积分,得到绕L2点的闭合轨道。以该闭合轨道为目标轨道,根据模型的动力学特点,设计变结构滑膜控制律。仿真结果表明,该控制律能很快消除飞行器入轨时位置、速度的偏差,使飞行器在目标轨道上稳定飞行。该文的结果可应用于对月球背面的定点观测或中继站。Station-keeping for orbits around the Lagrange point Lz in the Earth-Moon system need to allow for variation of the solar gravitation. The circular restricted three-body problem for the Earth-Moon system was showed to get the initial values for the differential corrections describe the solar gravitational perturbations. Then the symmetry of the dynamics equation was used to calculate a closed orbit around L2 by integrating along the negative and positive directions in time. A sliding mode controller was designed to track this closed orbit. Simulations show that this controller quickly eliminates the position and velocity decreases while getting into orbit to stabilize the spacecraft motion. These results can be applied to any fixed point observation or relay station behind the moon.

关 键 词：Lagrange点 HALO轨道 第四体引力 轨道保持 滑模控制 

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]