Abstract

In this paper, a novel multi-stage trajectory transfer and fixed-point landing time optimal guidance method for the lunar surface emergency rescue mission is proposed. Firstly, the whole process motion and dynamics model for the lunar surface emergency rescue with four stages are established. Then, in the initial orbit transfer phase, the Lambert algorithm based on "prediction + correction" is designed for the non spherical gravitational perturbation of the moon. In the powered descent phase, the Hamiltonian function is used to design a time suboptimal explicit guidance law that can be applied in orbit in real time. Finally, aiming at the multi-stage global time optimal guidance, the whole time process guidance law is obtained by establishing the allowable control set for each stage in the whole process. The simulation results show that compared with the piecewise optimal control method, the present method has better optimization effect and shorter whole process time. It is of great significance to the possible emergency rescue mission of manned lunar exploration in the future.

Highlights

  • [5] 庄学彬, 张耀磊, 李君, 等. 基于双冲量 Lambert 的快速定点入轨方法[ J] . 导弹与航天运载技术, 2015(3) : 1⁃4 ZHUANG Xuebin, ZHANG Yaolei, LI Jun, et al Method of fast fixed⁃point orbit transfer based on two⁃ impulse lambert[ J]

  • Fast guidance method of lunar landing based on dynamic programming

  • In the powered descent phase, the Hamiltonian function is used to design a time suboptimal explicit guidance law that can be applied in orbit in real time

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Summary

Introduction

西北工业大学学报 Journal of Northwestern Polytechnical University https: / / doi.org / 10.1051 / jnwpu / 20213910159 赵弘骞1,2, 代洪华1,2, 党朝辉1,2 (1.西北工业大学 航天学院, 陕西 西安 710072; 2.航天飞行动力学技术国家级重点实验室, 陕西 西安 710072) 12( u0 x0 + v0 y0 + z0 w0 ) tgo - 18( x20 + y20 + z20 ) = 0 ( 18) F2( Di ) = min{ u3( Cj,Di ) + f1( E) } (23) step4 对于初轨转移段,输入状态 X1,X2,tf,利 用图 3 的受摄动 Lambert 问题求解流程获得转移段

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