Fault diagnosing and tolerance control method for aircraft three-dimensional movement

Abstract

The invention provides a fault diagnosing and tolerance control method for aircraft three-dimensional 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 three-dimensional 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 more attention to it; fault diagnosis is extremely important for systems with high safety requirements, detecting system faults in time can make the self-repairing system reconstruct the control law in time, which 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...

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, resulting in the proposed fault-tolerant control scheme being different from the actual aircraft and difficult to apply, the present invention provides a three-dimensional aircraft 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 aircraft parameters and flight dynamics for the determined fault category Then re-model the catastrophic 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 quantity so that the output of the fault-free model meets the military standard requirements, and the The control input when the aircraft fails, which is composed of the control quantity and the non-artificial additional control quantity caused by the aircraft failure, makes the new model output stable when the aircraft fails

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