Direct self-adaptive fuzzy logic control method for suppressing wing rolling caused by high attack angle

An adaptive fuzzy and logical control technology, applied in the field of aircraft wing rock control, can solve problems such as limited control accuracy, complex controller design, and difficult solution of controller parameters, and achieve the effect of ensuring stability

Active Publication Date: 2021-03-19
GUANGDONG UNIV OF TECH
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Problems solved by technology

[0004] In order to solve the problems of complex controller design, difficulty in solving controller parameters and limited control accuracy in the existing control method for wing rock caused by high angle of attack, the present invention proposes a direct method for suppressing wing rock caused by high angle of attack. Adaptive fuzzy logic control method reduces the complexity and calculation amount of controller design, improves the reliability of the control system, and ensures the stability of the wing within any given error

Method used

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  • Direct self-adaptive fuzzy logic control method for suppressing wing rolling caused by high attack angle
  • Direct self-adaptive fuzzy logic control method for suppressing wing rolling caused by high attack angle
  • Direct self-adaptive fuzzy logic control method for suppressing wing rolling caused by high attack angle

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Embodiment 1

[0075] The positional relationship described in the drawings is only for illustrative purposes and cannot be construed as a limitation to this patent;

[0076] Such as figure 1 The schematic flow chart of the direct adaptive fuzzy logic control method for suppressing wing rock caused by high angle of attack includes the following steps:

[0077] S1. Establish the wing rock motion model; the expression of the wing rock motion model is:

[0078]

[0079] Among them, φ(t) represents the roll angle, u(t) represents the control signal, α represents the angle of attack of the aircraft in the steady state, represents an uncertain aerodynamic disturbance, K i ,i=0,1,...,4 represent known constants, satisfying:

[0080]

[0081]

[0082] Among them, q represents the free flow pressure, S represents the wing area, b represents the wing span, I xx Indicates the rolling moment of inertia, V indicates the flight speed, Indicates the moment coefficient, which is a dimensionl...

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Abstract

The invention provides a direct adaptive fuzzy logic control method for suppressing wing roll caused by a high attack angle, relates to the technical field of aircraft wing roll control, and solves the problems of complex controller design, difficulty in solving parameters of a controller and limited control precision in an existing control method for wing roll caused by the high attack angle. Themethod comprises the following steps: establishing a wing roll motion model, then converting the wing roll motion model into a nonlinear system model, and establishing a direct self-adaptive fuzzy logic system. According to the invention, by adopting direct self-adaptive fuzzy logic control, only one self-adaptive law exists, so that the calculation amount and complexity of controller design arereduced; and the direct adaptive fuzzy logic system is constructed by taking a wing rocking motion model as an analysis basis, so that strict convergence proof and stability analysis can be carried out, and the reliability of a closed-loop control system is greatly improved.

Description

technical field [0001] The invention relates to the technical field of aircraft wing rock control, in particular to a direct adaptive fuzzy logic control system for suppressing wing vibration caused by high angle of attack. Background technique [0002] Fighter is a military aircraft used to destroy enemy aircraft in the air. It is the main type of military air combat and occupies an irreplaceable position in both ground and air combat. The mission requirements of high-performance fighter jets are to operate normally at high angles of attack, and the unstable aerodynamic effects at high angles of attack can produce wing rocking phenomenon, which is manifested as limit period oscillation in roll. When a fighter jet enters the area of ​​high angle of attack, the aerodynamic and flight characteristics have undergone great changes, such as aerodynamic nonlinearity, asymmetry, cross-coupling, etc., which have caused a sharp change in the stability and maneuverability of the aircr...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0825Y02T90/00
Inventor黄凯赖冠宇
OwnerGUANGDONG UNIV OF TECH