Prediction model based hypersonic aircraft sliding-mode control method

A technology of hypersonic speed and control method, which is applied in the field of aircraft control and can solve problems such as complex design process and unfavorable engineering realization

CN102880053AActive Publication Date: 2013-01-16NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Publication Date
2013-01-16

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Abstract

The invention discloses a prediction model based hypersonic aircraft sliding-mode control method. The method is used for solving the technical problem of difficulty in engineering realization by existing hypersonic aircraft adaptive discrete control. The method includes: obtaining a strict feedback form of a height subsystem by reasonable assumption, and building a discrete form of an original system through an Eulerian method; building a four-step prediction model of the original system by unceasing forward prediction, wherein the model only includes an equation; enabling the prediction model to provide the relation of height output at a future time and current system state and control input, wherein the relation can be used for computing numerical values of lumped uncertainties of the system at the historical moment, and the numerical values are used for feedback design of a controller; and combining lumped nominal information further, and using a discrete reaching law to design the sliding-mode controller so that robustness of the system is improved. The prediction model based hypersonic aircraft sliding-mode control method has the advantages that the discrete prediction model is built to acquire system nominal and uncertain information, design of virtual control variables is not needed, the controller is simple and practical in design, and the method is suitable for engineering application.
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Description

technical field

[0001] The invention relates to a control method for a hypersonic aircraft, in particular to a sliding mode control method for a hypersonic aircraft based on a predictive model, and belongs to the field of aircraft control. Background technique

[0002] Due to its outstanding flight capability, hypersonic aircraft makes global real-time strike possible, so it has attracted widespread attention at home and abroad; NASA X-43A test flight successfully confirmed the feasibility of this technology; affected by its own complex dynamic characteristics and the airframe With the integrated design of the engine, the coupling between the elastic body, propulsion system and structural dynamics of the hypersonic vehicle is stronger, and the nonlinearity of the model is also higher; sensitive.

[0003] The control of hypersonic vehicles is mostly concentrated in the continuous domain; with the development of computer technology, the control system of hypersonic vehicles i...

Examples

Embodiment Construction

[0057] refer to figure 1 , the sliding mode control method of hypersonic aircraft based on predictive model of the present invention is realized through the following steps:

[0058] (a) Considering formula group (1)-(5) longitudinal channel dynamics model of hypersonic vehicle

[0059] V · = T cos α - D m - μ sin γ r 2 - - - ( 1 )

[0060] h · = V sin γ - - - ( 2 )

[0061] γ · = L ...