基于分段连续推力的晕轨道控制方法  

A Halo Orbit Control Method Based on Sectional Continuous Thrust

作　　者：晁宁[1] 李言俊[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《宇航学报》2011年第9期1925-1931,共7页Journal of Astronautics

基　　金：高等学校博士学科专项科研基金(20060699024)

摘　　要：基于小偏差理论,推导了三体动力学模型的误差线性模型,并将此假设下的控制归纳为终端固定的有限时间调节器问题。在此基础上,进一步利用该最优控制方法推导了晕轨道周期内的连续小推力控制方案,验证了控制加速度及状态量的收敛。同时针对整周期控制方式在超调后状态量收敛速度慢的问题,通过分段连续推力控制模式(Sectional Continuous Thrust Control,SCTC)来近似瞬时脉冲推力控制模式,给出了最短分段控制时间的计算方法。实验表明,SCTC模式加快了轨道状态的收敛速度。对于km级入轨偏差,通过1次控制即可使实际轨道收敛至标称轨道。Base on small deviation theory,an error linear model of three-body dynamics model is deduced.The control problem under the supposition is belong to the problem of filed and point regulator within finite time.Then continuous small thrust control law in a halo orbit period is deduced by using optimal control and the convergence of control acceleration and state is also validated.Aim at the problem that convergence rate of state in total period control mode after overshoot is low,method for calculating the shortest sectional control time is given by using the sectional continuous thrust control mode to approximate the instantaneous impulse thrust control mode.Experiment shows that the SCTC mode speeds up convergence of orbit state and the practical orbit is able to be converged to the standard orbit by using only one control at orbit insertion error of grade of kilometers.

关 键 词：晕轨道 平动点 最优控制 轨道保持 连续推力控制 

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]