A Sliding Mode Fault Tolerant Control Method for Spacecraft Attitude Integral Considering Actuator Failure

Abstract

The invention relates to a spacecraft attitude integral sliding mode fault tolerance control method taking consideration of a performer fault and provides a robustness attitude active fault tolerance control method based on an integral sliding mode surface for problems of the performer fault, external disturbance and control moment amplitude limits in a spacecraft attitude control process. The method comprises steps that firstly, a spacecraft attitude dynamics model taking consideration of the performer fault and containing external disturbance is established; secondly, on the condition that a performer is not in fault, a designed nominal controller can guarantee system stability, and input saturation amplitude limits can be easily satisfied through adjusting controller parameters; lastly, the fault information is introduced to design an integral sliding mode controller, robustness of external disturbance and the performer fault can be effectively improved, system stability is analyzed on the basis of an Lyapunov method. The method is advantaged in that stability of the attitude control system is guaranteed when a spacecraft operating on orbit generates the performer fault, and relatively strong fault tolerance capability and external disturbance robustness are realized.

Description

Technical field [0001] The invention relates to a spacecraft attitude integral sliding mode fault-tolerant control method considering actuator failure, which is mainly applied to attitude control system when actuator failure occurs in orbit operation of spacecraft and is subject to external disturbance. Background technique [0002] The continuous exploration of the unknown universe by mankind has promoted the vigorous development of the aerospace industry. The draft of my country's "13th Five-Year Plan" proposes that deep space exploration and spacecraft on-orbit service and maintenance systems are the six major "Technology Innovation 2030-Major Projects" "One, and plans to build a space station around 2020. As the most critical subsystem of the spacecraft, the attitude control system has the characteristics of complex structure, harsh working environment, unknown interference and multiple uncertain factors. It is one of the subsystems with the most failures. For spacecraft in o...

AI Technical Summary

Problems solved by technology

[0004] The technical solution of the present invention is to propose a robust attitude active fault-tolerant control method based on the integral sliding mode surface for the simultaneous existence of actuator failure, external disturbance and limited control torque amplitude during the spacecraft attitude control process; Solve the problem that the actuator fails when the spacecraft is in orbit and is subject to external disturbances and the control torque saturation is limited

Images