Method for selecting optimal error correction point of earth-moon L2 point transfer orbit

Abstract

The invention discloses a method for selecting an optimal error correction point of an earth-moon L2 point transfer orbit, which belongs to the technical field of aerospace. The implementation methodcomprises the following steps of establishing an earth-moon rotating coordinate system, and calculating an earth-moon L2 point nominal transfer orbit state transfer matrix, calculating the change condition of the error along with time according to the state transfer matrix, according to the state transfer matrix, establishing a function relationship between correction maneuver and correction timeand an orbit error, optimizing the correction time of the detector, and determining the optimal error correction point and correction speed increment of the correction speed increment and the terminalspeed increment by utilizing the function relationship, and enabling the detector to apply a speed increment at the optimal correction point to complete orbit correction of the earth-moon L2 point transfer orbit and complete earth-moon L2 point orbit transfer. According to the method, the speed increment required by correction can be minimized, and the method has the advantages of high correctionefficiency and reduction of correction fuel consumption. According to the method, the orbit transfer precision is improved by considering the influence of lunar attraction on the transfer orbit error.

Description

technical field [0001] The invention relates to a method for selecting an error correction point of an Earth-Moon L2 point transfer orbit, in particular to an error correction point selection and velocity increment evaluation method suitable for an Earth-Moon L2 point transfer orbit with errors, and belongs to the technical field of aerospace. Background technique [0002] In order to realize the detection of the far side of the moon, it is necessary to carry out relay communication and data transmission through the relay star. The L2 point of the Earth-Moon balance point is an ideal position for the relay star due to its better dynamic characteristics and geometrical position. Deploying the relay satellite in the periodical orbit at the L2 point of the Earth-Moon balance point requires the design of the transfer orbit. Among them, the fuel consumption and transfer time required for the near-moon flyby transfer using the dynamics of the three-body system are relatively low an...

AI Technical Summary

Problems solved by technology

[0004] The prior technology [2] (refer to: Li Mingtao, Zheng Jianhua. Research on the midway correction of the mission transfer orbit of the translation point [J]. Chinese Journal of Space Science, 2010, 30(6): 540-546.) studied the transfer of the Sun-Earth equilibrium point. For the error correction problem, it is proposed to use the method of reverse integration to convert the error correction into the design of the transfer orbit, but this method does not consider the optimization of the correction point and correction time, and it is mainly aimed at the transfer of the sun-earth balance point and the near-Earth-moon balance point next to the moon. divergence exists

Images