Earth-moon libration point interorbital transfer design method

A design method and translation point technology, applied to motor vehicles, space navigation equipment, space navigation equipment, etc., can solve problems such as the impact of unspecified detector fuel consumption, to avoid the impact of selection uncertainty, The effect of improving optimality

Active Publication Date: 2020-01-31
BEIJING SPACE TECH RES & TEST CENT
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Problems solved by technology

For the optimal transfer trajectory of fuel between different types of orbits near the 3 collinear translation points and 2 triangular translation points, the selection basis of the feature points and the influence of different feature p

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  • Earth-moon libration point interorbital transfer design method
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Embodiment Construction

[0064] In order to more clearly describe the embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings that are used in the embodiments. Apparently, the drawings in the following description are only some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to these drawings without creative efforts.

[0065] When describing the embodiments of the present invention, the terms "vertical", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", " The orientation or positional relationship expressed by "horizontal", "top", "bottom", "inner" and "outer" is based on the orientation or positional relationship shown in the relevant drawings, which are only for the convenience of describing the present invention and simplifying the description, and It is not to indicate or imply that the device or element referred to must have a particu...

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Abstract

The invention relates to an earth-moon libration point interorbital transfer design method. The method comprises the following steps that a, under the earth-moon mass center rendezvous coordinate system, an orbital kinetic equation of a detector is built; b, libration point invariant manifold data are stored; c, a transfer track splicing point range is searched; and d, a libration point interorbital optimal transfer track is determined. According to the libration point track invariant manifold state amount, splicing point positions of different track segments are rapidly determined, positionsof escape points and capture points are automatically adjusted, and the target track size are adjusted automatically, and the low-energy transfer track capable of meeting the task needs can be effectively designed.

Description

technical field [0001] The invention relates to the technical field of spacecraft orbit design and optimization, in particular to a design method for transfer between orbits of Earth-Moon translation points. Background technique [0002] There are five translation points in the Earth-Moon three-body system, among which L1 and L2 points are located on both sides of the moon, which are the best landing points for the implementation of lunar exploration missions. In 2011, NASA proposed to design an outpost plan at the Earth-Moon translation point, which can not only detect changes in the Earth-Moon space environment, but also serve as a transit station for future Earth-Moon space material transportation visits, Mars exploration, and manned asteroid missions. At the same time, there are often low-energy transfer orbits between the orbits of the translation points near the L1 and L2 points of the Earth-Moon system. Combining this type of orbit for extended tasks can effectively e...

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 曾豪黄震彭坤王平田林
Owner BEIJING SPACE TECH RES & TEST CENT
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