Detection, estimation and adjustment method of rigid spacecraft counteractive flywheel fault

Abstract

The invention discloses a detection, estimation and adjustment method of a rigid spacecraft counteractive flywheel fault. First an attitude dynamics model and a motion model of a rigid spacecraft are built; a mathematical model is built under the circumstance that an efficiency damage fault occurs in a rigid spacecraft counteractive flywheels; then a nonlinear fault detection observer and a self-adaptive nonlinear fault estimation observer are designed to be used for rapid detection and precise estimation of an unknown fault respectively; and finally, obtained fault estimation information is utilized to design a self-adaptive sliding-mode fault-tolerant controller. The detection, estimation and adjustment method of the rigid spacecraft counteractive flywheel fault considers transient performance of the fault-tolerant controller, and can accurately and rapidly detect, estimate and adjust the unknown fault under the circumstance that the counteractive flywheel efficiency damage fault occurs in the rigid spacecraft. Influence on a system caused by external disturbance is considered at the same time, and the system can perform design of a fault diagnosis module and the fault-tolerant controller relatively independently, thereby simplifying the design process, and facilitating realization in engineering.

Description

Technical field [0001] The invention belongs to the field of aerospace flight control, and specifically relates to a method for detecting, estimating and adjusting a rigid spacecraft reaction flywheel fault. Background technique [0002] Due to the diversity and complexity of spacecraft missions and their harsh working conditions (such as vacuum, weightlessness, high and low temperature, and strong radiation), the mechanical and electrical components of the spacecraft are facing aging, making the actuators prone to failure. [0003] Once a spacecraft component failure occurs, it will not only degrade the performance of the attitude control system, but also make the entire attitude control system unstable. In severe cases, the spacecraft's space mission will also fail. Therefore, the spacecraft requires the safety and reliability of the attitude control system to reach a very high level. However, the reaction flywheel in the spacecraft attitude control system is prone to failures (...

AI Technical Summary

Problems solved by technology

[0006] (1) The time required for the system to reach the sliding surface is difficult to meet the rapidity requirements

[0007] (2) It is difficult to achieve fast and accurate fault estimation, and the accuracy is difficult to be accurate

[0008] (3) It is difficult for the spacecraft attitude control system to meet high tolerance requirements for actuator failures

[0009] (4) The traditional design method is too complicated, making it difficult to realize in engineering

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