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Singular perturbation-based historical data learning self-adaptive control method of elastic aircraft

A technology of adaptive control and historical data, which is applied in the field of flight control and can solve problems such as difficulty in achieving nonlinear estimation effects.

Inactive Publication Date: 2019-11-15
NORTHWESTERN POLYTECHNICAL UNIV
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AI Technical Summary

Problems solved by technology

At present, most of the existing intelligent control researches update the weights based on the tracking error, which only guarantees the stability of the closed-loop system, and it is difficult to achieve the expected nonlinear estimation effect.

Method used

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  • Singular perturbation-based historical data learning self-adaptive control method of elastic aircraft
  • Singular perturbation-based historical data learning self-adaptive control method of elastic aircraft
  • Singular perturbation-based historical data learning self-adaptive control method of elastic aircraft

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Embodiment Construction

[0109] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0110] refer to figure 1 , the present invention is based on the singular perturbation elastic aircraft historical data learning adaptive control method applied to a class of hypersonic aircraft, through the following steps to achieve:

[0111] (a) Consider the elastic hypersonic vehicle longitudinal channel dynamic model:

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[0118] The kinematic model is composed of seven state quantities and two control inputs U=[δ e ,Φ] T Composition; where, V represents velocity, h represents height, γ represents track inclination, α represents angle of attack, q represents pitch angle velocity, η and Indicates the elastic mode, δ e Indicates rudder deflection angle, Φ indicates throttle valve opening; m, I yy and g denote the mass, the moment of inertia of the pitch axis, and the acceleration caus...

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Abstract

The invention relates to a singular perturbation-based historical data learning self-adaptive control method of an elastic aircraft. The method comprises the steps of decoupling a longitudinal channelmodel of the elastic aircraft to a speed sub-system and a height sub-system; decomposing a gesture sub-system to a slow sub-system and a fast sub-system by a singular perturbation algorithm, designing a rudder deflection angle controller of the slow sub-system by dynamic surface control, estimating system uncertainty information by a neural network, acquiring on-line data, building a forecast error, combining and tracing an error, adjusting weight updating rule of the neutral network, and designing a sliding-mode self-adaptive algorithm for mode suppression according to a fast time mark partof representing system elastic mode; designing aperture of a throttle valve of a speed sub-system by a PID strategy, achieving tracing control of height and speed, and finally, applying the control method to a hypersonic aircraft elastic body model.

Description

technical field [0001] The invention relates to an aircraft control method, in particular to a singular perturbation-based elastic aircraft historical data learning adaptive control method, which belongs to the field of flight control. Background technique [0002] Existing elastic aircraft control studies mostly ignore the elastic mode and directly design the controller for the rigid body. However, the object is only regarded as a pure rigid body for control, which cannot meet the needs of high-precision control; some scholars also regard the elastic mode as a disturbance. , through compensating control to realize the control of the elastic part. However, this approach lacks in-depth analysis and research on the dynamics of elastic bodies. Backstepping control is widely used in aircraft control, but there is a "complexity explosion" problem in traditional design, so dynamic surface design and command filtering design are applied to reduce design complexity. In view of the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 许斌寿莹鑫
Owner NORTHWESTERN POLYTECHNICAL UNIV
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