Electromagnetic force-based cluster spacecraft magnetic moment optimal allocation method

Abstract

The invention provides an electromagnetic force-based cluster spacecraft magnetic moment optimal allocation method. A magnetic moment allocation problem is converted into an optimization problem; by establishing an objective function, calculating interference moments and analyzing constraint conditions, currents in axial coils of two spacecrafts are calculated by adopting a simulated annealing algorithm; optimal allocation of magnetic moments is realized; and the speed is higher. The proposed magnetic moment optimal allocation method enables a total interference moment of an interference moment of a geomagnetic field and an interference moment between the spacecrafts to be minimal; and through simulation analysis of magnetic moment allocation of two situations that the magnetic moments ofthe two spacecrafts are not restrained and assumed to be same, a conclusion is obtained that enabling the magnetic moments of the two spacecrafts to be same is more favorable for realizing better allocation, and the energy consumption is balanced.

Description

technical field [0001] The invention belongs to the technical field of magnetic moment distribution method research, in particular to an electromagnetic force-based optimal magnetic moment distribution method for cluster spacecraft. Background technique [0002] Cluster spacecraft refers to a group of spacecraft composed of multiple modular satellites with specific functions, which can use satellite self-organization capabilities to replace manual operations, realize the functions of a whole star, and complete space missions more efficiently. Spacecraft control based on electromagnetic force generally uses three orthogonal coils to achieve relative control of satellite formation. Researches on electromagnetic control, electromagnetic rendezvous and docking, electromagnetic formation, and electromagnetic drag of swarm spacecraft can learn from each other. The optimal distribution of magnetic moments of cluster spacecraft based on electromagnetic force is to study how to dist...

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Problems solved by technology

Ahsun et al. ("Control of electromagnetic satellite formations in near-earth orbits") and Lian Kefei et al. ("Electromagnetic Spacecraft Formation Position Tracking Adaptive Cooperative Control") both transformed the control assignment problem into An optimization problem, which optimizes the disturbance torque of the geomagnetic field, but the introduction is relatively brief

Abbott et al. ("Computing minimum-power dipole solutions for interdipole forces using nonlinear constrained optimization with application to electromagnetic formationflight") used the sequential quadratic programming method to solve the magnetic moment to minimize the power consumption of the coil, but this method did not consider the geomagnetic field and the distance between the spacecraft. The influence of the disturbance torque on the spacecraft system

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