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Adaptive control method for morphing aircraft based on aerodynamic parameter estimation

A variant aircraft and adaptive control technology, applied in the field of flight control, can solve the problem of unknown aerodynamic parameters of the variant aircraft, and achieve the effect of improving control performance and effective tracking

Active Publication Date: 2021-04-20
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problem that the aerodynamic parameters of the variant aircraft are unknown, the present invention proposes an adaptive control method for the variant aircraft based on the estimation of aerodynamic parameters

Method used

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  • Adaptive control method for morphing aircraft based on aerodynamic parameter estimation
  • Adaptive control method for morphing aircraft based on aerodynamic parameter estimation
  • Adaptive control method for morphing aircraft based on aerodynamic parameter estimation

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Embodiment Construction

[0077] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0078] refer to figure 1 , the present invention is based on the variable aircraft adaptive control method of aerodynamic parameter estimation and is applied to the variable-sweep wing aircraft, and is realized by the following steps:

[0079] (a) Considering the longitudinal channel dynamics model of the variable-sweep wing aircraft

[0080]

[0081]

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[0085] Among them, F Ix , F Ikz , F Iz and M Iy Indicates the moment of inertia caused by the deformation process, and its expression is

[0086]

[0087] The dynamic model contains five state variables X=[V,h,α,γ,q] T and two control inputs U=[δ e ,T] T , where V represents velocity, h represents altitude, α represents angle of attack, γ represents track angle, q represents pitch angular velocity, δ e Indicates rudder deflection angle, T indicates thrust; D, L...

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Abstract

The invention relates to an adaptive control method for a variant aircraft based on aerodynamic parameter estimation. The method decouples the longitudinal channel model of the variant aircraft into a velocity subsystem and an altitude subsystem, adopts dynamic inverse control for the velocity subsystem, and adopts dynamic inverse control for the altitude subsystem. The system is controlled by backstepping method. In order to effectively deal with the unknown aerodynamic function in system dynamics, the dynamic model is transformed into a linear parameterized form in which the known state quantity item is multiplied by the unknown aerodynamic parameter item, and an adaptive update law is designed to estimate the unknown parameter part. Estimate the information to design the controller to realize the effective tracking of the system height and speed command.

Description

technical field [0001] The invention relates to an aircraft control method, in particular to an adaptive control method for a variant aircraft based on aerodynamic parameter estimation, and belongs to the field of flight control. Background technique [0002] The morphing aircraft can change the shape of the wing through the actuating mechanism or smart materials, which has the advantages of different aircraft, adapts to changing mission environments, and increases flight stability and maneuverability. During the process of aircraft deformation, the physical parameters, center of gravity, aerodynamic parameters, and moment of inertia of the aircraft will change greatly. It is impossible to establish a single model to describe the entire deformation process, and a fixed controller cannot effectively control it. The current research strategy is based on methods such as CFD simulation to obtain the functional expressions of aerodynamic parameters related to deformation, and to ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 许斌王霞
Owner NORTHWESTERN POLYTECHNICAL UNIV