A Design Method of the Earth-Moon Translational Point Transfer Orbit Constrained by the Moon's Borrowing Force

Abstract

The invention relates to a method for designing an earth-moon libration point transfer orbit via moon leveraging constraint, and belongs to the field of design and optimization of spacecraft orbits. The method comprises the following steps: selecting an injection point position of a target Halo orbit and an expected moon leveraging constraint size, and integrating the state parameter of an injection point via an equation (1) until a spacecraft arrives at an expected moon leveraging position. The state parameter of the injection point is corrected and regulated by a related optimization algorithm, so that the state of a leveraging position satisfies the constraint condition of an equation (3), and then the increment size of a maneuvering speed necessary for the spacecraft for entering the Halo orbit is determined. Since the moon leveraging constraint condition and the Halo orbit injection point and other parameters are selected, a transfer orbit with low energy consumption and capable of satisfying task requirements can be effectively designed.

Description

technical field [0001] The invention relates to a method for designing a transfer orbit of an earth-moon translation point constrained by the moon's force, and belongs to the field of spacecraft orbit design and optimization. Background technique [0002] In recent years, the Halo orbit near the L2 translation point (EML2) of the Earth-Moon system has become a research focus in the field of aerospace engineering and applications. Through the EML2 point Halo orbit, the probe can observe the far side of the moon and provide navigation strategies for lunar landing missions. At the same time, around the EML2 point, a transfer orbit with low energy consumption can be designed to reach the moon, Mars and other planets, which can provide the best foothold for the exploration of the deep space environment (Xu Ming, Xu Shijie. Earth-Moon system translation point and Halo orbit Applied research on [J]. Acta Astronautica Sinica. 2006,27(4):695-699). Therefore, in order to reduce the ...

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Problems solved by technology

For example, Zazzera uses a hybrid optimization method of genetic algorithm and sequential quadratic programming to analyze multiple indirect transfer orbits without considering the moon's leverage (Zazzera F B, Topputo F, Massari M. Assessment of mission design including utilization of liberation points and weak stability boundaries [R].ESTEC Contract No.18147 / 01 / NL / MV,2004); Parker based on the weakly stable boundary and the invariant manifold transfer strategy, through the invariant manifold connecting the sun-earth system and the earth-moon system, designed a Long-duration flight transfer orbit from low earth orbit to Halo orbit at EML2 (Parker J S. Low-Energy Ballistic Lunar Transfers[D].Colorado:University of Colorado,2007); Gordon uses stable manifold theory and lunar leverage technology to construct Li proposed a two-pulse transfer orbit, but the ability to reduce fuel consumption is limited; Li designed a three-pulse transfer orbit scheme with low fuel consumption on the basis of Gordon, but did not give a selection strategy for the Halo orbit entry point (HOI) There are certain limitations in the engineering application of the lunar leverage constraint and its influence considered in the analysis (Gordon D P.Transfers to earth-moon L2halo orbits using lunar proximity and invariant manifolds[D].Indiana:Purdue University,2008 ; Li M T, Zheng JH. Impulsive lunar halo transfers using the stable manifolds and lunar flybys[J].Acta Astronautica,2010,66:1481-1492)

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