Diagnosis and compensation method for rigid spacecraft multi-reaction flywheel fault

Abstract

The invention discloses a diagnosis and compensation method for a rigid spacecraft multi-reaction flywheel fault. According to method, attitude dynamics and kinematics mathematical models for the rigid spacecraft multi-reaction flywheel fault are established; a fault diagnosis unit is designed to detect and estimate an unknown fault; and a non-singular fast terminal sliding mode technology is adopted to design an active fault-tolerant control scheme on the basis of fault estimation information obtained from the fault diagnosis unit. With the diagnosis and compensation method of the invention adopted, the fault of a rigid spacecraft can be diagnosed and compensated when the rigid spacecraft has a multi-reaction flywheel fault, or the reaction flywheels of the rigid spacecraft are saturated;inertia uncertainty and the adverse effects of external disturbances on the system in a design process can be processed at the same time; and the fault diagnosis unit and the fault-tolerant controller are designed independently, and therefore, design complexity can be reduced, and the requirements of engineering applications can be better satisfied.

Description

technical field [0001] The invention belongs to the field of aerospace flight control, and relates to a method for diagnosing and compensating for a multi-reaction flywheel fault of a rigid spacecraft. Background technique [0002] In highly complex control systems such as spacecraft and aircraft, safety and reliability are particularly important, because failures in such systems may cause a significant decline in system performance or even make the entire system unstable, which may eventually lead to The entire mission fails. The attitude control subsystem of a spacecraft plays an important role in many space missions, and the life of the attitude control components essentially determines the life of the spacecraft. The degradation of the attitude control subsystem may seriously interfere with the execution of space missions, and its failure is fatal to the spacecraft. [0003] The actuator is one of the important components of the attitude control system. Under the comm...

AI Technical Summary

Problems solved by technology

[0006] (1) Traditional fault estimation methods rely on the upper bound information of generalized perturbation, and the accuracy of fault estimation is difficult to guarantee

[0007] (2) It is difficult to deal with multi-reaction flywheel faults, reaction flywheel saturation, inertia uncertainty and external disturbances in rigid spacecraft attitude control systems at the same time

[0008] (3) The design of the traditional fault-tolerant control method is too complicated, which increases the complexity of the system and is difficult to apply in engineering practice

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