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Reverse Design Method of Spacecraft Moon-Earth Transfer Orbit

A technology for transferring orbits and orbits, which is applied in design optimization/simulation, special data processing applications, etc., and can solve problems that cannot reflect the geometric characteristics of lunar-earth transfer orbits, cannot estimate the initial value of the control variables of the lunar core segment, and select the parameters 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: 2022-02-11
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 no regularity, cannot reflect the geometric characteristics of the lunar-earth transfer orbit, and cannot perform a simple initial value estimation of the control variables of the lunar core segment

Method used

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  • Reverse Design Method of Spacecraft Moon-Earth Transfer Orbit
  • Reverse Design Method of Spacecraft Moon-Earth Transfer Orbit
  • Reverse Design Method of Spacecraft Moon-Earth Transfer Orbit

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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 reverse design method of a lunar-earth transfer orbit of a spacecraft, comprising the steps of: a. establishing a lunar-earth transfer orbit reverse flight process, selecting variable control variables; b. performing an alignment search to determine the lunar-earth transfer orbit The near-earth orbit surface; c. Carry out the constrained search of the departure parameters of the orbit around the moon, and determine the near-lunar orbit surface of the lunar-earth transfer orbit; d. Search the lunar-earth transfer orbit to meet the constraints of the landing field coplanarity and re-entry point; e. Orbital simulation to obtain the moon-earth transfer orbit. According to the reverse design method of the moon-earth transfer orbit of the spacecraft in the present invention, the orbit reverse deduction method is adopted, the solution process is simple, the search speed is fast, and the convergence is good.

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 ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20
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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