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

A technology of fault diagnosis and fault-tolerant control, which is applied in the direction of adaptive control, general control system, control/regulation system, etc., and can solve the problem of fault-tolerant control scheme deviating from the actual aircraft, aircraft high angle of attack motion fault diagnosis and fault-tolerant control lack of technical methods , Difficult to apply and other issues

Active Publication Date: 2013-06-12
XIAN FEISIDA AUTOMATION ENG
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  • Claims
  • Application Information

AI Technical Summary

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 switching model, the method according to the aircraft without failure Fault diagnosis based on the discriminant model and state combination index; 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-model the sudden change system after the fault occurs , to obtain a new model description when the aircraft fails; the design method of the fault-tolerant controller is that the designed control quantity makes the output of the non-fault model meet the military standard requirements, and the control quantity and the non-artificial additional control quantity caused by the aircraft failure are jointly composed The control input when the 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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  • Fault diagnosing and tolerance control method for aircraft large-angle-of-attack movement switching model
  • Fault diagnosing and tolerance control method for aircraft large-angle-of-attack movement switching model
  • Fault diagnosing and tolerance control method for aircraft large-angle-of-attack movement switching model

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Embodiment Construction

[0034] 1. The non-linear switching model of high angle of attack motion when the aircraft has no faults is:

[0035]

[0036] In the formula: state variables h, V T , α, β, p, q, r represent flight altitude, flight speed, airflow angle of attack, sideslip angle, roll angular velocity, pitch angular velocity, yaw angular velocity; g is gravity acceleration; Q, S, m, I x , I y , I z , I zx Respectively represent dynamic pressure, wing area, aircraft mass, moment of inertia around the X axis of the body axis, moment of inertia around the Y axis of the body axis, moment of inertia around the Z axis of the body axis, and moment of inertia around the XZ axis of the body axis Product; C x (α,β,δ),C y (α,β,δ),C z (α, β, δ) represent longitudinal force, lateral force and normal force respectively; C L (α,β,δ),C N (α,β,δ),C M (α, β, δ) are roll moment, yaw moment, and pitch moment respectively; δ is the control quantity; usually the sideslip angle is usually less than 90°, a...

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Abstract

The invention provides a fault diagnosing and tolerance control method for an aircraft large-angle-of-attack movement switching 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 switching 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 de...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02G05B13/04
Inventor 史忠科
Owner XIAN FEISIDA AUTOMATION ENG
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