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

A system reconstruction and spacecraft technology, which is applied in the direction of space navigation vehicle guidance devices, space navigation aircraft, and aircraft, etc. It can solve problems affecting the safety of spacecraft in orbit, the loss of attitude reference of spacecraft, and the inability to effectively provide redundant backup, etc. problem, to achieve the effect of extending the life of the gyroscope

Active Publication Date: 2019-10-15
中国人民解放军63789部队
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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 axe...

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

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[0031] The present invention will be further described below in conjunction with the accompanying drawings and embodiments, and the present invention includes but not limited to the following embodiments.

[0032] In view of the actual demand of the three-axis zero-momentum spacecraft on-orbit bias momentum control, in order to realize the switching of the spacecraft from zero momentum control to bias momentum control, it is necessary to ensure that the spacecraft has gyro-axis alignment under bias momentum control. According to the spacecraft bias momentum control target, by establishing a flywheel group linear programming model under inequality constraints, and formulating a flywheel reorganization strategy based on optimization criteria, the bias momentum output in the direction of the pitch axis can be maximized, and the flywheel control system can be reconstructed. Analysis of telemetry data shows that the satellite attitude and pointing accuracy is stable within 1.5 degre...

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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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Application Information

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IPC IPC(8): B64G1/28
CPCB64G1/285
Inventor 卞燕山陈军王小乐张莹田志海胡亚军郑惠强王刚郭静
Owner 中国人民解放军63789部队
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