Adaptive-Based Fault Compensation and Disturbance Suppression Method for Aircraft Control System

Abstract

The invention provides a method for fault compensation and disturbance suppression of an aircraft control system based on self-adaptation. Based on the disturbance model and failure model, a dynamic model that affects the input of the aircraft control system is established; the basic controller is designed according to the dynamic model; the adaptive controller is designed based on the failure modes; the integrated controller is designed based on adaptive weighted fusion. The invention can effectively suppress the gust disturbance and compensate the failure when the aircraft control system has gust disturbance and unknown actuator failure, so as to ensure that the aircraft control system has the desired closed-loop stability and output tracking performance, thereby achieving stable and progressive tracking control targets , improve the effect of fault-tolerant control, and ensure the flight safety of the aircraft.

Description

technical field [0001] The invention relates to the technical field of automatic control, in particular to an adaptive-based aircraft control system fault compensation and disturbance suppression method. Background technique [0002] With the development of science and technology, some new performance-critical application systems with large-scale system dynamics have emerged, such as aerospace vehicles, nuclear reactors, micro-electromechanical systems, and smart grid systems. The structure of these new systems has the characteristics of large working range, complex system dynamic range, and many components, which make them extremely vulnerable to the influence of the external environment. Among them, the influence of uncertain external environment on the system can be characterized by many uncertain external disturbances, such as unfavorable airborne conditions such as gusts, turbulence, and freezing in the aerospace field. Usually, these uncertain external disturbances ma...

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Problems solved by technology

With the rapid development of performance-critical systems represented by aircraft, the system model is more complex, and its characteristics such as nonlinearity, multi-variables, strong coupling, and uncertainty become more prominent. These factors make the existing control theory and technology unable to meet The requirements for safe flight of aircraft urgently require new control theories and methods to improve the safety and reliability of the control system, so as to effectively avoid catastrophic accidents and major economic losses

[0003] Although a lot of feasible progress has been made in the research of actuator fault compensation for flight systems, there are still many open problems, especially the control problem without considering the actual unknown mismatch disturbance and multiple uncertain actuator faults.

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