宇航学报

宇航学报 ›› 2021, Vol. 42 ›› Issue (12): 1542-1549.doi: 10.3873/j.issn.1000-1328.2021.12.007

• 制导、导航、控制与电子 • 上一篇    下一篇

预测与反演交会制导的燃料消耗遗传算法寻优

谭天乐   

  1. 1.上海航天控制技术研究所，上海 201109； 2.上海市空间智能控制技术重点实验室，上海 201109
  • 收稿日期:2021-02-17 修回日期:2021-05-18 出版日期:2021-12-15 发布日期:2021-12-15
  • 基金资助:
    上海市自然科学基金(19ZR1423200)

Optimization of Propellant Consumption Based on Genetic Algorithm for Spacecraft Rendezvous under Model Predictive and Inversive Control

TAN Tian le   

  1. 1. Shanghai Aerospace Control Technology Institute, Shanghai 201109, China; 2. Shanghai Key Laboratory of Space Intelligent Control Technology, Shanghai 201109, China
  • Received:2021-02-17 Revised:2021-05-18 Online:2021-12-15 Published:2021-12-15

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摘要： 为了在航天器的多脉冲交会制导过程中寻找推力器的最佳工作时间以实现燃料消耗最优，基于模型预测与反演制导控制，提出了燃料消耗的遗传寻优方法。该方法根据轨控速度总量设计遗传个体的适应度函数；以推力器在一个控制周期中是否工作设置基因位的0-1状态，构造二进制编码形式的遗传个体；以等距稀疏控制的启发式方法生成初始种群；采用罚函数实现工程约束；通过选择淘汰、交叉变异等遗传操作的迭代，实现制导时长、控制周期确定情况下，多脉冲空间交会制导的燃料消耗寻优。仿真结果表明，遗传算法寻优得到的推力器工作模式具有较为显著的特征，可以有效减少制导中推力器工作时间，降低制导所需轨控速度总量，从而降低燃料消耗，同时仍然保证制导精度。


关键词: 交会对接, 多脉冲制导, 模型预测与反演控制, 燃料消耗, 遗传算法, 轨迹优化

Abstract: In order to find the best on/off sequence of thruster in multi pulse guidance for rendezvous of spacecraft to realize propellant consumption optimization, a genetic algorithm based on model the predictive and inversive control is proposed. In this method, the fitness function of genetic individual is designed according to total speed increment needed for orbit control. The genetic chromosome is constructed in binary coding form, each gene position is set to be 0 or 1, corresponding to whether the thruster works in a control cycle. The heuristic strategy of equidistant sparse control is used to generate the initial population, and the penalty functions are used to satisfy the engineering constraints. By iterative operation of genetic crossover, mutation and selection, the propellant consumption of multi pulse rendezvous is optimized. Simulation results show that the on/off sequence of thruster optimized by the genetic algorithm has obvious characteristics, which can effectively shorten the working time of thruster in guidance and reduce the speed increment needed for orbit control, thus reducing the propellant consumption and still ensuring the guidance accuracy.


Key words: Rendezvous and docking, Multi pulse guidance, Model predictive and inversive control (MPIC), Propellant consumption, Genetic algorithm, Trajectory optimization

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