基于分段连续推力的中途修正方法

摘要

Base on small deviation theory,the three-body dynamic equations are linearized,and the error linear model of three-body dynamic model is deduced.Then,continuous small thrust controlling law by using optimal control in a transfer period is deduce and the astringency of acceleration and state is also validated.At the same time,aim at the problem that speed of state astringing by total period control mode after overshoot is low,method for calculating the shortest segmental control time is given by using segmental continuous thrust control mode to simulate instantaneous impulse mode.Experiment shows that SCTC mode accelerate astringing speed of orbit state and practical orbit is able to astringe to standard orbit by using only one control with the entering orbit error grade of kilometers.%基于小偏差理论,对无摄三体动力学方程沿标称轨道线性化,推导了三体动力模型的误差线性模型.在此基础上,进一步利用该最优控制方法推导了转移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(Segmental Continuous Thrust Control,SCTC)来近似瞬时脉冲推力控制模式,并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.