Fault diagnosing and tolerance control method for aircraft longitudinal movement

Abstract

The invention provides a fault diagnosing and tolerance control method for aircraft longitudinal movement. The method comprises the following steps of according to a model and a state combination index discriminant when an aircraft has no fault, carrying out the fault diagnosing; and when the aircraft has a fault, firstly, classifying the fault, analyzing the influence of the whole-aircraft parameters and the flight dynamic properties according to the determined fault type, and remodeling an abrupt-change system after the fault occurs, so as to obtain a new model description when the aircraft has the fault. The design method of a tolerance controller is characterized in that the output of a fault-free model can meet the requirements of military standards by the designed control amount; and when the aircraft has the fault, the new model output is stable by the control input which is formed by the control amount and the non-artificial additional control amount caused by the aircraft fault.

Description

technical field [0001] The invention relates to an aircraft fault diagnosis and fault-tolerant control design method, in particular to an aircraft longitudinal motion fault diagnosis and fault-tolerant control method. Background technique [0002] Military aircraft is an important combat weapon, and civil aircraft is an important means of transportation. It plays an increasingly important role in national defense and people's daily life and work. The research on fault diagnosis of aircraft systems has become more and more important. More and more people pay attention to it; fault diagnosis is extremely important for systems with high safety requirements, timely detection of system faults, so that the self-repairing system can reconstruct the control law in time, and can avoid system collapse and the resulting material losses and casualties. [0003] The fault detection and diagnosis technology dominated by analytic redundancy was first developed in the United States in the e...

AI Technical Summary

Problems solved by technology

[0005] In order to solve the technical problem that the existing fault-tolerant control technology only adjusts the input coefficient of the aircraft, and does not consider the aerodynamic characteristics in the design, which makes the fault-tolerant control scheme given difficult to be used in practice, the present invention provides an aircraft longitudinal motion fault Diagnosis and fault-tolerant control method. This method performs fault diagnosis according to the model and state combination index discriminant formula when the aircraft has no faults; when the aircraft fails, first classify the faults, and then analyze the overall parameters and flight dynamics characteristics of the aircraft for the determined fault category , and then re-model the mutation system after the fault occurs to obtain a new model description when the aircraft fails; the design method of the fault-tolerant controller is to design the control amount so that the output of the non-fault model meets the military standard requirements, and the control amount The control input when the aircraft fails and the non-artificial additional control amount caused by the aircraft failure make the new model output stable when the aircraft fails

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