在轨目标逼近远程导引律设计

Design Long-range Guidance Law of Orbital Target Approach

利用最优多脉冲方法,对目标航天器逼近过程的远程导引段轨道进行设计。基于Lawden主矢量理论,解决固定时间、燃料最省的逼近轨道问题。通过仿真分析了固定初始条件时燃料消耗量随着转移时间的变化关系,对于燃料和时间均有约束的情况,给出了求解燃料最省和时间最小的多目标优化问题的方法。这一研究对于评估具体任务的燃料消耗和转移时间有重要意义。

The transfer trajectory of the orbital target approach in the long - range guidance phase is designed using the optimal multiple-impulse method. According to Lawden＇s primer vector theory, the problem of fixed-time fuel-optimal orbit is solved. By analyzing the simulation results, the effect of transfer time on fuel expenditure with fixed initial conditions is summarized, and the solution method to the multi-objective optimization problem of the fuel expenditure and transfer time which both constrained to some limits is obtained. The study is valuable for assessing preliminary fuel requirement and transfer time.