Fault diagnosing and tolerance control method for aircraft large-angle-of-attack movement ternary number model

Abstract

The invention provides a fault diagnosing and tolerance control method for an aircraft large-angle-of-attack movement ternary number model. 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; 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; and the fault diagnosing and the tolerance control can be directly carried out on the aircraft large-angle-of-attack flight.

Description

technical field [0001] The invention relates to an aircraft fault diagnosis and fault-tolerant control design method, in particular to a fault diagnosis and fault-tolerant control method for a large angle of attack motion ternary model of an aircraft. 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 deve...

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Problems solved by technology

[0005] In order to solve the 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 given fault-tolerant control scheme is difficult to apply from the actual aircraft. In particular, many fault-tolerant control methods use linear inequality or non-abrupt System, the lack of technical methods for the fault diagnosis and fault-tolerant control of aircraft high angle of attack motion, the present invention provides a fault diagnosis and fault-tolerant control method for aircraft high angle of attack motion ternary model, the method according to The model and state combination index discriminant at the time of failure is used for fault diagnosis; when the aircraft fails, first classify the faults, and then analyze the influence of the aircraft's overall parameters and flight dynamics characteristics for the determined fault category, and then re-analyze the mutation system after the fault occurs. Modeling to obtain a new model description when the aircraft fails; the design method of the fault-tolerant controller is to design the control amount to make the output of the non-fault model meet the military standard requirements, and the control amount is the same as the non-artificial additional control amount caused by the aircraft failure. The control input when the composed aircraft fails makes the output of the new model stable when the aircraft fails; and it can directly diagnose the aircraft's high angle of attack flight fault and perform fault-tolerant control

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