Fault tolerance flight control system and method based on control surface faults

Abstract

The invention provides a fault tolerance flight control system based on control surface faults. The fault tolerance flight control system based on control surface faults comprises a sensor, a fault detection and insulation module, a monitor module, a controller module and a control distribution module, wherein the sensor is arranged at the corresponding part of an airplane body; the fault detection and insulation module transmits an airplane state parameter estimation value to the controller module, judges the health situation of control surfaces and the types of the generated faults, calculates the probability of the type of faults on each control surface, transmits the probability to the monitor module, detects the deviation angle of each control surface to obtain a deviation angle estimation value of each control surface, and transmits the deviation angle estimation value of each control surface to the monitor module; the monitor module determines the faults positions of the control surfaces, and provides a control distribution basis for the control distribution module; the controller module generates a virtual control command vector, and transmits the vector to the control distribution module as virtual control input; the control distribution module calculates the control surface deviation angle vector of each control surface deviation angle given value. When the control surface faults occur, based on fault detection and diagnosis results, the fault tolerance flight control system based on control surface faults provided by the invention compensates faults, thereby guaranteeing the continuous and safe flight of an airplane.

Description

technical field [0001] The invention belongs to the technical field of aircraft fault-tolerant control, in particular to a fault-tolerant flight control system and method based on rudder surface failure. Background technique [0002] A fault-tolerant flight control system refers to a flight control system with redundant capabilities. When some components of the aircraft fail or even fail, the fault-tolerant flight control system can still perform according to the original performance index or slightly reduced performance index (within the acceptable range) within) to complete control tasks safely. Common methods for fault-tolerant flight control system design include: multi-model switching and tuning, multi-model adaptive control, model reference adaptive control, interactive multi-model, control assignment, sliding mode control, model predictive control, feature structure configuration, model reference And dynamic inverse, neural network, etc. The multi-model switching an...

AI Technical Summary

Problems solved by technology

The advantage of the multi-model adaptive control method is that it can respond quickly when the parameters change, so it has a faster fault isolation speed than other methods that do not have a multi-model structure, but this method will lead to an increase in the amount of calculation required for each filter , and produces unsatisfactory results when encountering insufficient conformance with predefined failure assumptions

The model reference adaptive control method is used in situations where damage faults or structural faults need to be fault-tolerant. The purpose is to make the output of the system track the output of the reference model. The disadvantage of this method is that when a fault or failure occurs, it will make the system’s The parameter value changes suddenly, so the adaptive algorithm cannot quickly identify the new faulty system in a short period of time, so it cannot guarantee that the controller can control the system stably

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