基于脉冲初值的小推力转移轨道优化研究

针对小推力转移轨道优化过程往往忽略初值多样性的现状,研究了基于不同脉冲初值的小推力转移轨道优化问题。基于直接法的离散思想建立了小推力转移轨道优化模型,提出了基于粒子群和序列二次规划的组合优化算法,以地球1∶1共振近地小行星2016HO3交会任务为例,将3种典型的脉冲轨道作为初值设计了燃料最优小推力转移轨道。仿真结果表明:3种初值轨道优化得到了2个小推力转移发射窗口,两者燃料消耗差距不超过6%。不同的初值对小推力轨道的整体性能指标影响较小,但开关机时刻和推力方向的变化会产生较大差异,从而得到不同的最优控制曲线。

Study on Low-Thrust Transfer Trajectory Optimization Based on Impulse Initial Value

Considering the fact that the diversity of initial values is often neglected in the optimization process of the low-thrust transfer trajectory, the low-thrust transfer trajectory optimization with different initial impulse values is studied in this paper. Firstly, a low-thrust transfer trajectory optimization model based on the direct method is established. Then, a combinatorial optimization algorithm based on particle swarm optimization and sequential quadratic programming is proposed. Finally, the asteroid 2016HO3 rendezvous mission is selected as a simulation example, and the optimization results of the low-thrust transfer orbit are analyzed with single-revolution double-pulse, triple-pulse and multi-revolution double-pulse as initial values. The results show that two launch windows are obtained from three initial values, with the fuel consumption gap of less than 6%. Different initial value inputs will cause large differences in switch time and the change of thrust direction, but only a subtle distinction in overall performance indexes, thus different optimal control curves can be obtained.