Reconstruction method of electromagnetic spacecraft configuration with low fuel consumption and stable process

Abstract

The invention belongs to the technical field of electromagnetic spacecraft, and particularly relates to a reconstruction method of electromagnetic spacecraft configuration with low fuel consumption and stable process. The method comprises the main steps of: (S1) calculating an initial relative equilibrium configuration and a target relative equilibrium configuration of an electromagnetic spacecraft formation system; (S2) designing a time interval as a connection time frame of an expected initial relative equilibrium unstable manifold and a target relative equilibrium stable manifold; and (S3)selecting an unstable manifold in the global manifold of the initial relative equilibrium configuration and a certain amount of discrete state points on the stable manifold in the global equilibrium of the target relative equilibrium configuration, establishing a scalar optimization objective function about the deviation between state points, designing a pulse speed increment and an electromagnetic magnetic moment to make the scalar optimization objective function approach 0 to achieve the reconstruction of two spacecrafts. The electromagnetic force manipulation is introduced in the configuration reconstruction design to fully utilize the advantage without consumption of fuel, and the stability is good.

Description

technical field [0001] The invention belongs to the technical field of electromagnetic spacecraft, in particular to an electromagnetic spacecraft configuration reconstruction method with low fuel consumption and stable process. Background technique [0002] With the enhancement of the ability of micro-nano spacecraft to perform on-orbit missions, it has gradually become a typical model to realize the needs of a single large spacecraft mission or a new concept on-orbit mission through a cluster of micro-nano spacecraft. Through micro-nano spacecraft clustering and reconfiguration to achieve configuration flexibility, the on-orbit mission capability, accuracy, robustness, and upgradeability can be significantly improved. At present, many studies have been carried out on the reconfiguration of spacecraft clusters under the action of conventional inertial thrust, and some optimal design methods have been proposed; the introduction of on-board controllable electromagnetic devices...

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Problems solved by technology

[0003] Existing technologies mainly start from the reconfiguration planning method, less consideration is given to the inherent characteristics of the control object itself (especially the micro-nano electromagnetic spacecraft), and the reconfiguration optimization scheme designed has the disadvantages of insufficient mining potential and only sub-optimum, including: ( 1) The characteristics of electromagnetic spacecraft manipulation are not fully utilized, and the configuration reconstruction consumes too much fuel; (2) The characteristics of the configuration reconstruction process are not enough, and there may be dynamic instability characteristics in the process

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