Angular momentum distribution method of redundant flywheel combination based on modified pseudo-inverse matrix

Abstract

The invention relates to an angular momentum distribution method for a redundant flywheel combination based on a modified pseudo-inverse matrix, and the method comprises the steps: S1, calculating a reference driving moment of each flywheel in the redundant flywheel combination according to a three-axis instruction moment based on a flywheel angular momentum distribution algorithm combining the pseudo-inverse matrix with zero motion; S2, according to the reference driving torque of each flywheel, the current angular momentum of each flywheel and the upper limit of the angular momentum of eachflywheel, constructing a saturation variable, and evaluating the degree of each flywheel close to the saturation of the angular momentum; calculating a performance index correction coefficient by utilizing the saturated variable, and obtaining a corrected pseudo-inverse matrix by utilizing the saturated variable and the performance index correction coefficient; and S3, calculating the driving torque of each flywheel in the redundant flywheel combination according to the corrected pseudo-inverse matrix. According to the method, the problem that the angular momentum utilization rate of a singleflywheel is remarkably reduced after zero motion is introduced into a redundant flywheel combination can be effectively solved, and the output time of a given moment can be remarkably prolonged.

Description

technical field [0001] The invention relates to a method for distributing angular momentum of a redundant flywheel combination, in particular to a method for distributing angular momentum of a redundant flywheel combination based on a modified pseudo-inverse matrix. Background technique [0002] At present, the reaction flywheel based on the principle of angular momentum exchange to output torque is the most widely used attitude control actuator on three-axis attitude stabilization satellites. However, modern space missions put forward higher requirements on the life of the satellite. Therefore, in order to improve the reliability of the system, more than three flywheels are usually installed on the satellite to form a redundant flywheel combination as the actuator of the attitude control system. Since the number of flywheels is greater than the dimensionality of the output torque, the redundant flywheel combination can also bias the flywheel speed near the optimal operating...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a method for distributing angular momentum of a redundant flywheel combination based on a modified pseudo-inverse matrix, which can effectively solve the problem that the angular momentum utilization rate of a single flywheel significantly decreases after the redundant flywheel combination introduces zero motion, and can Significantly extend the output time for a given torque

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