Reverse design method for lunar-terrestrial transfer orbit of spacecraft

A transfer orbit and reverse design technology, applied in design optimization/simulation, instrumentation, calculation, etc., can solve the problem of inability to reflect the geometric characteristics of the lunar-earth transfer orbit, the inability to estimate the initial value of the control variables of the lunar core segment, and the parameter selection of the lunar core segment There are no problems such as regularity, and the effect of simple initial value estimation, fast search speed and good convergence is achieved

Active Publication Date: 2019-02-15
BEIJING SPACE TECH RES & TEST CENT
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Problems solved by technology

There are two shortcomings in this method: 1) The solution process is complicated, and iterative solutions are required in the double two-body model and the precise model; The selection of α has n

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  • Reverse design method for lunar-terrestrial transfer orbit of spacecraft
  • Reverse design method for lunar-terrestrial transfer orbit of spacecraft
  • Reverse design method for lunar-terrestrial transfer orbit of spacecraft

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specific Embodiment approach

[0044] According to above-mentioned scheme of the present invention, provide a specific embodiment as follows:

[0045] According to the above-mentioned step a of the present invention, the orbit reverse thrust flight process of the moon-earth transfer orbit is established. Let the initial parameter be: departure time t around the moon TEI =29Jun 2014 02:00:00.000UTCG, orbit height h LLO =100km, inclination angle i around the moon LLO = 160°, the terminal condition is the re-entry point height h EI = 120km, re-entry angle γ EI =-6.0°, re-entry point geocentric orbit inclination i EI =20°, the latitude and longitude of the landing field (α=110°E, δ=20°N), and the lunar-earth transfer time is about 3 days. The initial value of the control variable is taken as t f2 = 2Jul 2014 02:00:00.000UTCG, a LEO =6428.137km,Ω LEO =90°,

[0046] According to the above-mentioned step b of the present invention, the target constraint is set to the perimonthly point time t 0 = t T...

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Abstract

The invention relates to a method for reverse design of lunar-terrestrial transfer orbit of a spacecraft, comprising the following steps: a. Establishing a lunar-terrestrial transfer orbit reverse flight flow, and selecting variable control variables; (b) performing a quasi-lunar search to determine that near-Earth end orbital surface of the lunar-terrestrial transfer orbit; (c) performing constraint search on that lunar orbit departure parameters to determine the lunar orbital surface near the lunar end of the lunar-terrestrial transfer orbit; (d) performing lunar-to-ground transfer orbit searching to meet that constraint of coplanar landing site and reentry point; E. performing Orbit simulation to obtain a lunar-to-terrestrial transfer orbit. The inverse design method of the lunar-terrestrial transfer orbit of the spacecraft adopts the method of orbit inversion, and has the advantages of simple solving process, fast searching speed and good convergence.

Description

technical field [0001] The invention relates to the technical field of lunar-earth transfer orbits of spacecraft, and relates to a method for designing lunar-earth transfer orbits of spacecraft during the process of returning to the earth from the moon, in particular to a reverse design method for spacecraft lunar-earth transfer orbits. Background technique [0002] The lunar-earth transfer orbit refers to the orbit where the spacecraft escapes from the moon and returns to the earth after the lunar-earth transfer acceleration in the orbit around the moon. For manned missions to the moon or lunar sampling return missions, after completing the mission on the lunar surface and returning to the orbit around the moon, it is necessary to design a suitable moon-earth transfer orbit so that the spacecraft can apply a pulse at a specified time to transfer from the orbit around the moon to the earth for re-entry Boundary point, and use atmospheric deceleration to return safely to the ...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 彭坤孙国江黄震王平田林李志杰奉振球
Owner BEIJING SPACE TECH RES & TEST CENT
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