Method for designing earth-moon libration point transfer orbit via moon leveraging constraint

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 the hybrid optimization method of genetic algorithm and sequential quadratic programming to analyze multiple indirect transfer orbits without considering the leverage of the moon (ZazzeraFB, TopputoF, MassariM.Assessment of mission design including utilization of libration points and weakness boundaries[R]. , 2004); Parker designed a long-duration transfer orbit from low earth orbit to EML2 point Halo orbit by connecting the invariant manifold of the sun-earth system and the earth-moon system based on the weakly stable boundary and the invariant manifold transfer strategy ( ParkerJS.Low-EnergyBallisticLunarTransfers[D].Colorado:University ofColorado,2007); Gordon constructed a two-pulse transfer orbit using the stable manifold theory and lunar leverage technology, but the ability to reduce fuel consumption is limited; Li is on the basis of Gordon , designed a three-pulse transfer orbit scheme with low fuel consumption, but did not give the selection strategy and analysis of the Halo orbit entry point (HOI) and the lunar leverage constraints and their impacts considered, there are certain limitations in engineering applications Limitations (GordonDP.Transferstoearth-moonL2haloorbitsusinglunarproximityandinvariantmanifolds[D].Indiana:PurdueUniversity,2008;LiMT,ZhengJH.Impulsivelunarhalotransfersusingthestablemanifoldsandlunarflybys[J].ActaAstronautica,2010,646:14281-1)

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