An Optimal Allocation Method of Cluster Spacecraft Magnetic Moment Based on Electromagnetic Force

Abstract

The present invention provides a method for optimal distribution of magnetic moments of clustered spacecraft based on electromagnetic force, which transforms the problem of magnetic moment distribution into an optimization problem, and uses simulated annealing algorithm to calculate the The current in the coils of each axis in the device realizes the optimal distribution of the magnetic moment, which is faster; the proposed optimal distribution method of the magnetic moment minimizes the total interference torque of the earth's magnetic field interference torque and the interference torque between the spacecraft; through simulation analysis The distribution of magnetic moments under the conditions of not constraining and assuming that the magnetic moments of the two spacecraft are equal, it is concluded that making the magnetic moments of the two spacecraft equal is more conducive to achieving a better distribution, 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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