Flexible spacecraft multi-domain dependent robust fault-tolerant control method based on input time-varying delay

Abstract

The invention relates to a flexible spacecraft multi-domain dependent robust fault-tolerant control method based on input time-varying delay, comprising the following steps: first, taking flexible vibration as external disturbance, and establishing a flexible spacecraft state space model containing external disturbance and input delay through deduction by use of a Lagrange method; then, establishing a fault model, integrating the fault model into a flexible spacecraft state model needing fault tolerance, and converting an actuator partial failure fault-tolerant control problem into an uncertain parameter robust control problem according to the fault model; and finally, designing a state feedback passive fault-tolerant controller based on a linear matrix inequality approach by combining delay-dependent Liapunov functional and uncertain parameter robust H-infinity control. The method has the advantages of simple design and easy implementation, is applicable to fault-tolerant control under the condition that a flexible spacecraft has both input delay and actuator partial failure in the field of aerospace, and can keep a system asymptotically stable and suppress external interference.

Description

technical field [0001] The invention relates to a multi-boundary dependent robust fault-tolerant control method for a flexible spacecraft with input time-varying time-delay, which is applied to the attitude fault-tolerant control of input time-delay and partial failure of actuators of flexible spacecraft on orbit. Background technique [0002] With the continuous development of aerospace technology, the functions of spacecraft are diversified. There are more and more spacecraft with large flexible accessories (such as large solar panels, etc.). The impact of flexible vibration on the realization of high-precision attitude control of spacecraft Can not be ignored. At the same time, due to the longer and longer design life of spacecraft and the longer on-orbit operation time, higher requirements are put forward for the reliability and safety of the control system of flexible spacecraft in orbit. However, due to the long-term operation of the spacecraft in the harsh environmen...

AI Technical Summary

Problems solved by technology

But the fault-tolerant control of flexible spacecraft with flexible vibration, input time-delay and partial actuator failure has not been extensively studied

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