Nonlinear Geometry Control of Spacecraft for Halo Orbit Maintenance
An innovative method for halo orbit maintenance is proposed in this paper using continuous low thrust.The circular restricted three-body problem with Sun and Earth as the two primaries is considered.The equations of motion are derived and the location and stability of the collinear equilibrium point discussed.A nonlinear geometry control law is designed to enable a spacecraft to track desired nominal orbit near halo orbit of the L1 libration point in the Sun-Earth system.The controller is designed such that the actual orbit tracks a nominal orbit with good accuracy.Numerical results employing this method demonstrate the potential of this method.
JIA Jie MA Kemao YAO Yu
Control and Simulation Center,School of Astronautics,Harbin Institute of Technology,Harbin 150080,P. Control and Simulation Center,School of Astronautics,Harbin Institute of Technology,Harbin 150080,P.
国际会议
The 30th Chinese Control Conference(第三十届中国控制会议)
烟台
英文
1-6
2011-07-01（万方平台首次上网日期，不代表论文的发表时间）