火力与指挥控制2012，Vol.37Issue(5)：71-76,6.
基于分段连续推力的中途修正方法
Method of Midcourse Correction Based on Segmental Continuous Thrust
摘要
Abstract
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Key words
three-body problem/midcourse correction/continuous thrust/optimal control/orbit control分类
航空航天引用本文复制引用
晁宁,李言俊..基于分段连续推力的中途修正方法[J].火力与指挥控制,2012,37(5):71-76,6.基金项目
高等学校博士学科专项科研基金资助项目(20060699024) （20060699024）
