基于分段连续推力的中途修正方法(英文)  

Method of Midcourse Correction Based on Segmental 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：《火力与指挥控制》2012年第5期71-76,共6页Fire Control & Command Control

基　　金：高等学校博士学科专项科研基金资助项目(20060699024)

摘　　要：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(Segm en ta l Con tinuous T hrust Con tro l,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。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.

关 键 词：三体问题 中途修正 连续推力 最优控制 轨道控制 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]