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A Model Reference Adaptive Robust Control Method for Aircraft

A technology of adaptive control and adaptive controller, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problem of strong nonlinearity of aircraft dynamics system, uncertainty of aircraft parameters, high frequency of control signals Oscillation and other problems, to achieve the effect of fast parameter self-adaptation, simple and easy-to-use control method, and improved stability

Active Publication Date: 2018-08-14
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0002] During the flight of the aircraft, its load changes, system aging, actuator failure, and external environmental disturbances will lead to strong nonlinearity in the aircraft dynamics system, large parameter change ranges, and parameter jumps. It is not possible to simply use a single It is described by a linear model, which brings great challenges to the design of the control system of the aircraft
[0003] Model reference adaptive control has always been an effective method to solve the problem of aircraft parameter uncertainty and jump. Among them, in order to solve the uncertainty problem caused by the large range of parameter changes, a large adaptive rate is usually used to ensure fast response, but A large adaptive rate will cause high-frequency oscillation of the control signal, which will stimulate the dynamic characteristics of the model, resulting in system instability. This defect has become a limitation for the wide application of model reference adaptive control.

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  • A Model Reference Adaptive Robust Control Method for Aircraft
  • A Model Reference Adaptive Robust Control Method for Aircraft
  • A Model Reference Adaptive Robust Control Method for Aircraft

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[0102] In order to better illustrate the purpose and advantages of the present invention, the technical solutions are further described in conjunction with examples.

[0103] Applying the aircraft robust model reference adaptive control method based on linear matrix inequality proposed in the present invention to the roll wing dynamics model with strong nonlinearity and uncertain parameters,

[0104]

[0105] in, state quantity x 1 is the roll angle φ, the state quantity x 2 is the roll angular velocity

[0106] θ T =[0.2314,0.7848,-0.0624,0.0095,0.0215]

[0107] The reference model is selected as the natural vibration frequency ω n =0.4rad / s A typical second-order system with a damping ratio ξ=0.707, the reference command r(t) selects an amplitude of 15°, and the frequency is square wave. According to the control method and system proposed by the present invention, the control gain matrix K can be obtained 1 =[0.16,0.57],K 2 =0.16, K 3 =[-85.3538,-40.4107], s...

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Abstract

The invention discloses an aircraft robust model reference adaptive control method and system based on a linear matrix inequation. The method includes: establishing an aircraft dynamical model, and selecting a reference model; setting a state feedback controller, an adaptive controller and a linear matrix inequation-based robust controller according to the dynamical model and the reference model, thereby acquiring linear state feedback control law, adaptive control law and robust correction items, and introducing them to the aircraft dynamical model to obtain the linear matrix inequation-based robust model reference adaptive controller, and controlling an aircraft through this controller.

Description

technical field [0001] The invention belongs to the technical field of automatic control, and relates to an aircraft control system and a control method, in particular to a robust model reference adaptive control system and method based on linear matrix inequalities. Background technique [0002] During the flight of the aircraft, its load changes, system aging, actuator failure, and external environmental disturbances will lead to strong nonlinearity in the aircraft dynamics system, large parameter change ranges, and parameter jumps. It is not possible to simply use a single It is described by a linear model, which brings great challenges to the design of the control system of the aircraft. [0003] Model reference adaptive control has always been an effective method to solve the problem of aircraft parameter uncertainty and jump. Among them, in order to solve the uncertainty problem caused by the large range of parameter changes, a large adaptive rate is usually used to en...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/04
Inventor 赵良玉石忠佼
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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