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Adaptive Control Method for Data Screening of Elastic Aircraft Based on Singular Perturbation Decomposition

A technology of adaptive control and data screening, applied in the field of flight control

Active Publication Date: 2019-10-11
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
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Problems solved by technology

[0005] In order to solve the problem of the flight control of the elastic aircraft system under the nonlinear unknown situation, the present invention proposes an adaptive control method for elastic aircraft data screening based on singular perturbation decomposition

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  • Adaptive Control Method for Data Screening of Elastic Aircraft Based on Singular Perturbation Decomposition
  • Adaptive Control Method for Data Screening of Elastic Aircraft Based on Singular Perturbation Decomposition
  • Adaptive Control Method for Data Screening of Elastic Aircraft Based on Singular Perturbation Decomposition

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Embodiment Construction

[0114] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0115] refer to figure 1 , the present invention is based on singular perturbation decomposition elastic aircraft data screening adaptive control method is applied to a class of hypersonic aircraft, through the following steps to achieve:

[0116] (a) Consider the elastic hypersonic vehicle longitudinal channel dynamic model:

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[0123] 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 cau...

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Abstract

The present invention decouples a longitudinal channel model of an elastic aircraft into a speed subsystem and a height subsystem; decomposes an attitude subsystem into a slow variable subsystem and afast variable subsystem through a singular perturbation algorithm, adopts dynamic surface to control and design a rudder angle controller of the slow variable subsystem, and uses a specific algorithmto screen online data quality, records high quality data and discards inferior data, and stores online in a dynamic history stack, infers invariant state dependency attribute of the system accordingto data information, to construct a new prediction error, combines the specifically selected online record data with real-time data to adjust weight update law of the neural network, and designs a sliding mode adaptive control algorithm to perform modal suppression aiming at fast-changing time-scale portion of an elastic mode of a representation system; and adopts a PID strategy to design throttleopening degree aiming at the speed subsystem, realizes tracking control of height and speed, and finally applies the control method to a hypersonic aircraft elastomer model.

Description

technical field [0001] The invention relates to an aircraft control method, in particular to an elastic aircraft data screening adaptive control method based on singular perturbation decomposition, belonging to the field of flight control. Background technique [0002] Existing studies on aircraft elastic body control mostly ignore elastic modes and directly design controllers for rigid bodies. Disturbance, elastic part control is realized through compensation control, but this processing method lacks in-depth analysis and research on elastic body dynamics. 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 nonlinearity of the aircraft system, the intelligent control technology based on neural network approximation learning has been widely concerned. At present, most existing intelligent co...

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Application Information

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IPC IPC(8): G05B13/04G05D1/08
CPCG05B13/027G05B13/042G05D1/0825
Inventor 许斌寿莹鑫
Owner NORTHWESTERN POLYTECHNICAL UNIV
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