月地应急返回轨道优化设计

doi:10.3969/j.issn.1001-506X.2020.02.22

Abstract

Abstract:

The three-impulse trajectories are optimally designed for the emergency return problem in the manned lunar landing mission. The motion equations of lunar return trajectories are adopted in the spherical frame based on the model of the circulunar restricted three body problem. The Moon-Earth emergency return trajectories concerning the constraints of circular orbit plane, minimum safe distance with respect to the Moon and terminal perigee height are optimized globally by using the MultiStart algorithm. The effectiveness and reliability of the proposed approach are demonstrated by the simulation tests. Finally, according to a great deal of simulation results by the method, the effects of different orbit parameters on optimization objective are analyzed. The research conclusions can provide references for the design of emergency return trajectory scheme in the manned lunar landing mission in the future.

Key words: manned lunar landing, emergency return, circular restricted three body problem (CR3BP), global optimization

CLC Number:

V412.4

Lin LU, Haiyang LI, Jianghui LIU, Luyi YANG. Optimal design of the Moon-Earth emergency return trajectories[J]. Systems Engineering and Electronics, 2020, 42(2): 420-426.

Figures/Tables 11

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References 30

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算法	θ₀/(°)	ϕ₀/(°)	Δt₁/d	Δt₂/d	Δt₃/d	Δv₁/(km/s)	Δv₂/(km/s)	Δv₃/(km/s)	Δv/(km/s)
MultiStart算法	171.22	59.67	1.44	0.85	3.71	0.614	0.153	0.323	1.09
遗传算法	164.25	71.90	0.91	0.61	4.48	0.635	0.206	0.569	1.41

算法	脉冲序号	Δv_r	Δv_θ	Δv_ϕ	Δv_i
MultiStart算法	1	0.000	0.095	0.607	0.614
	2	0.046	0.130	0.067	0.153
	3	0.109	0.132	0.274	0.323
遗传算法	1	0.000	0.136	0.620	0.635
	2	0.103	0.079	0.160	0.206
	3	0.055	0.555	0.114	0.569

设计参数	计算结果
返回出发时刻	2028-01-27 07:19:15
Δt₁/d	1.34
Δt₂/d	0.77
Δt₃/d	3.89
Δv₁/(km/s)	0.631
Δv₂/(km/s)	0.160
Δv₃/(km/s)	0.269
Δv/(km/s)	1.060

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Optimal design of the Moon-Earth emergency return trajectories

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