Angular Momentum Distribution Method for Redundant Flywheel Combination Based on Modified Pseudoinverse Matrix

Abstract

The present invention relates to a method for distributing angular momentum of a redundant flywheel combination based on a modified pseudo-inverse matrix, comprising: S1, an algorithm for distributing angular momentum of a flywheel based on a pseudo-inverse matrix combined with zero motion, and calculating a redundant flywheel combination according to a three-axis command torque The reference driving torque of each flywheel in ; S2, according to the reference driving torque of each flywheel, the current angular momentum of each flywheel and the upper limit of angular momentum of each flywheel, construct a saturation variable, and evaluate the degree of each flywheel approaching angular momentum saturation degree; use the saturation variable to calculate the performance index correction coefficient, and use the saturation variable and the performance index correction coefficient to obtain the revised pseudo-inverse matrix; S3, according to the revised pseudo-inverse matrix, calculate the drive of each flywheel in the redundant flywheel combination moment. The invention can effectively solve the problem that the utilization rate of the angular momentum of a single flywheel significantly decreases after introducing zero motion into the redundant flywheel combination, and can significantly prolong the output time of a given torque.

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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