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
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[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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