摘要
针对航天器轨道交会的脉冲推力模型与实际发动机连续推力模型不相符的问题,研究一种脉冲变轨策略的工程实现方法,使脉冲变轨策略可应用于工程实际.基于Lambert飞行时间定理和遗传算法,研究航天器最优脉冲变轨策略.根据脉冲变轨优化的结果,采用迭代制导算法研究脉冲变轨工程化问题.仿真结果验证了迭代制导算法在航天器轨道交会中的有效性.
The discrepancies between impulsive thrust model and continuous thrust model have greatly limited the application of impulsive strategy on spacecraft rendezvous trajectory engineering. Based on Lambert theorem and genetic algorithm, an optimal impulsive rendezvous trajectory is designed. Accord- ing to the results, an engineering realization method is implemented via iterative guidance algorithm. The simulation results show that the method is effective.
出处
《空间控制技术与应用》
CSCD
北大核心
2015年第3期14-17,37,共5页
Aerospace Control and Application
关键词
航天器交会
脉冲交会
迭代制导
orbital rendezvous
impulsive rendezvous
iterative guidance
