Libration point spacecraft formation reconfiguration method based on self-adaption agent model

Abstract

The invention relates to the technical field of spacecraft formation reconfiguration, and provides a libration point spacecraft formation reconfiguration method based on a self-adaption agent model. The method comprises the steps that 100, a sun-terrestrial system libration point nearby spacecraft formation controlled kinetic equation is built; 200, according to the spacecraft formation reconfiguration mission requirement, an optimization target is selected to obtain the optimization problem of spacecraft formation reconfiguration; 300, the self-adaption agent model of spacecraft formation reconfiguration is built, and the optimal reconfiguration track of a spacecraft formation is obtained through the self-adaption agent model; 400, the value range of a variable in the self-adaption agent model is narrowed, the step 300 is repeated in sequence, and the validity of the self-adaption agent model is verified. On the premise of the high computational efficiency, the formation reconfiguration result very close to the actual optimal solution can be obtained.

Description

technical field [0001] The invention relates to the technical field of spacecraft formation reconfiguration, in particular to a reconfiguration method of a translation point spacecraft formation based on an adaptive agent model. Background technique [0002] Spacecraft formation refers to the joint formation of multiple spacecraft into a virtual large-scale spacecraft to complete tasks that are difficult for a single spacecraft. organization to ensure the completion of its tasks. When the target formation configuration is known, it is only necessary to solve the optimal trajectory of the spacecraft formation reconfiguration according to the optimal control theory. Most of the current literature and scientific research work belongs to the case of known target configuration. However, in many emergencies, the final configuration of the spacecraft needs to be determined according to the task of the formation and the actual situation. At this time, the problem of formation reco...

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Problems solved by technology

[0003] The present invention mainly solves the problem that in the process of spacecraft formation reconstruction near the translation point in the sun-earth system, the prior art method of obtaining the optimal reconstruction configuration and optimal reconstruction trajectory cannot solve the contradiction between calculation eff

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