Method for reconstructing flywheel system under on-orbit biased-momentum control switching of spacecraft

Abstract

The invention provides a method for reconstructing a flywheel system under on-orbit biased-momentum control switching of a spacecraft. A flywheel group linear programming model under an inequality constraint condition is established according to a biased momentum control target of the spacecraft, a flywheel recombination strategy is made according to an optimization criterion, the output maximization of the biased momentum in a direction of a pitch axis is achieved, and a flywheel control system is reconstructed. According to the method, a flywheel recombination biased angular momentum outputmodel under the constraint condition can be quickly established, the iterative optimal solution is carried out by adopting a simplex method, and a gyroscope is replaced to ensure normal on-orbit operation of a satellite.

Description

technical field [0001] The invention belongs to the field of on-orbit spacecraft measurement and control management, and is applicable to the reconfiguration of a flywheel control system for three-axis zero-momentum spacecraft on-orbit bias momentum control. Background technique [0002] On-orbit spacecraft usually adopt a three-axis stable wheel control system with zero momentum control. Due to factors such as the harsh space environment, component aging, and mechanical structure wear and tear, component failures of the attitude control system occur frequently in orbit. In order to meet the mission requirements of the spacecraft to the greatest extent and prolong the use efficiency of the spacecraft, it is necessary to use the remaining normal components of the spacecraft to modify the attitude control software through uplink injection under the condition of some attitude control device failures, so as to realize the function during the failure period. Substitution or down...

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Problems solved by technology

[0003] The traditional method is to switch the backup parts after the failure of the attitude control device. In this method, when multiple gyroscopes on the orbit fail, only three gyroscopes are left to provide velocity information (the three gyroscopes have components in the three axes of pitch, roll, and yaw). ), it cannot effectively provide redundant backup, which will affect the safety of the spacecraft in orbit, and in severe cases, the spacecraft will lose its attitude reference and change from the general attitude towards the ground to the attitude towards the sun

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