Continuous low-thrust interplanetary transfer orbit optimization method and device

Abstract

The invention relates to the technical field of spaceflight, in particular to a continuous low-thrust interplanetary transfer orbit optimization method and device. The method comprises the following steps: constructing a preset parameter-containing transfer orbit model; optimizing the performance indexes of the preset parameter-containing transfer orbit model under different launching time information through a simulated annealing method to obtain optimal launching time information; constructing a homotopy mapping performance index according to a first start-end and end-end boundary conditioncorresponding to the optimal transmitting time information; and solving the fuel optimal two-point boundary value problem according to the homotopy mapping performance index to obtain a fuel optimal continuous low-thrust interplanetary transfer orbit. According to the method, then analytical method based on the preset parameter-containing transfer orbit model is combined with the simulated annealing method to search optimal launching time information in a large-range window, the calculation amount is reduced, the calculation speed and the calculation efficiency are improved, the orbit detailsare determined through the homotopy method after the optimal launching time information is determined, the convergence is improved and the calculation difficulty and the calculation amount are reduced.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a method and device for optimizing a continuous low-thrust interplanetary transfer orbit. Background technique [0002] In the earlier deep space exploration activities, the design of the deep space exploration orbit was based on the two-body problem and the Hohmann orbit transition. There were no other dynamic problems to be solved, and only the geometrical Kepler orbits needed to be spliced. And because the Kepler orbits all appear in the form of conic curves, this kind of orbit design method is called the conic curve splicing method. This design method also has its limitations and needs to be based on the following assumptions: [0003] 1. The thrust of the orbit control engine of the spacecraft is relatively large, which can be approximately regarded as pulse thrust. [0004] 2. The time for the spacecraft to be near the equilibrium point between the two celestial bodies ...

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Problems solved by technology

[0007] The purpose of the present invention is to provide a continuous low-thrust interplanetary transfer orbit optimization method and device to solve the techni

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