Analytic low-thrust circular orbit different-plane intersection optimization method

An optimization method and low-thrust technology, applied in the field of aerospace navigation control, can solve the problems of many variables, time-consuming integration, and difficulty in obtaining the optimal rendezvous trajectory, etc., and achieve the effect of improving the solution efficiency

Pending Publication Date: 2022-07-08
CHINA XIAN SATELLITE CONTROL CENT
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to provide an analytical method for optimizing the rendezvous of different planes of circular orbits with small thrust, which solves the problems

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  • Analytic low-thrust circular orbit different-plane intersection optimization method
  • Analytic low-thrust circular orbit different-plane intersection optimization method
  • Analytic low-thrust circular orbit different-plane intersection optimization method

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Embodiment

[0112] Suppose the initial mass of the spacecraft is 500kg, the specific impulse is 1000s, and the thrust is 0.5N. The target orbit is required to rendezvous after 14 days. The number of local orbits and target orbits is as follows

[0113] Table 1 Epoch is the initial time of the local star and the target orbit

[0114] A(km) e i (degree) Ω(degree) ω (degree) M (degree) ben star 7100 0 98 0 0 0 Target 7140 0 98.1 1 0 0

[0115] The solution steps are as follows (1) First, calculate the orbital difference between the local star and the target at the rendezvous time as [△a 0 ,△e x0 ,△e y0 ,△i 0 ,△Ω 0 ,△u 0 ]=[40km, 0, 0, 0.1 degree, 1 degree, 0, 0]. (2) Set k thrust Discrete 51 numbers with an interval of 0.02 between 1 and 0, and solve the equation system of formula (7) in turn to obtain k thrust When =0.38, the equivalent speed increment is 93.78m / s, which is the optimal value. (3) Calculate u 1 ,α 1 ,u 2 ,α 2 ,△t ...

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Abstract

The invention discloses an analytic low-thrust circular orbit different-plane intersection optimization method, which comprises the following steps of: firstly, obtaining an input spacecraft initial orbit, a target orbit needing to be intersected and a specified intersection moment, and calculating an orbit element difference between the spacecraft initial orbit and the target orbit needing to be intersected at the given intersection moment under the condition that the spacecraft is free of thrust and the target orbit needing to be intersected under the condition that the spacecraft is free of thrust; a simplified model for describing the intersection trajectory of the different planes of the small-thrust circular orbits is obtained; secondly, establishing a fixed thrust starting coefficient, and optimizing to obtain an optimal thrust starting coefficient, a semi-major axis, an inclination angle and right ascension variation of an ascending node; obtaining the phase difference of the rendezvous time relative to the target orbit needing rendezvous; obtaining a new dip angle and ascending node right ascension variation; and finally, outputting a corresponding small thrust control rate and a rendezvous transfer orbit. The method solves the problems that in the prior art, a parameter optimization method is time-consuming in integration and too many in solving variables, and the optimal rendezvous trajectory is not easy to obtain.

Description

technical field [0001] The invention belongs to the technical field of aerospace navigation control, and in particular relates to an analytical method for optimizing the cross-section of circular orbits with small thrust. Background technique [0002] In space operations or debris removal missions, spacecraft need to rendezvous targets and perform various operations in the most fuel-efficient manner. Compared with traditional chemical propulsion, electric propulsion has the advantage of high specific impulse, but the thrust is small, the orbital transfer time is long, and the optimization calculation is difficult. The indirect optimization method can only meet the necessary conditions of optimality, so the solution is easy to fall into the local optimum, and it takes a long time to repeatedly integrate the orbit. Existing parameter optimization methods also have time-consuming integration, too many variables to solve, and it is not easy to obtain optimal intersection trajec...

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/242B64G1/24B64G1/245Y02T90/00
Inventor 黄岸毅李恒年
Owner CHINA XIAN SATELLITE CONTROL CENT
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