GEO-satellite orbit-transfer strategy computing method and system based on particle swarm algorithm and medium

Abstract

The invention discloses a GEO-satellite orbit-transfer strategy computing method and system based on the particle swarm algorithm and a medium. The GEO-satellite orbit-transfer strategy computing method includes the following steps that a satellite original orbit parameter, a satellite dynamical model, the ignition number N required when an orbit of a satellite is transferred to a GEO and semi-major-axis expected values after every-time ignition are preset; according to the satellite orbit parameter and the satellite dynamical model of every-time ignition, every-time ignition timing and the every-time ignition direction serve as optimization variables, the semi-major-axis expected values after every-time ignition serve as constraints, and every-time ignition optimization is carried out according to the particle swarm algorithm to obtain an every-time ignition optimization result. According to the GEO-satellite orbit-transfer strategy computing method and system based on the particle swarm algorithm and the medium, the ignition timing and the ignition direction serve as the optimization variables, propellant consumption serves as an objective function, original particle populationsare set, evolutionary computation is carried out according to the algorithm, expectation solutions are more rapidly obtained, and computing efficiency is improved.

Description

technical field [0001] The invention belongs to the field of GEO satellite orbit change calculation in which a carrier rocket launches a satellite to a supersynchronous transfer orbit, and in particular relates to a particle swarm algorithm-based GEO satellite orbit change strategy calculation method, system and medium. Background technique [0002] At present, the launch process of geostationary orbit satellites is usually that the launch vehicle carries the satellite into space and transports the satellite to the supersynchronous transfer orbit. After the satellite and rocket are separated, the satellite needs to use its own engine to ignite and change orbit, and transfer to the geosynchronous orbit. [0003] The thrust of the engine carried by the satellite itself is limited. Considering factors such as engine ablation, the duration of a single ignition is also limited. Therefore, it is usually necessary to perform multiple ignition orbit changes, each ignition for a perio...

AI Technical Summary

Problems solved by technology

[0005] In the prior art, there is no technology to quickly find the optimal solution in the orbit change ignition strategy that meets the requirements

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