Prediction model based hypersonic aircraft Kriging control method

Abstract

The invention discloses a prediction model based hypersonic aircraft Kriging 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; computing historical information of lumped uncertainties of the system according to the prediction model, and performing constructive estimations for future uncertainties by a Kriging method by means of Gaussian random distribution assumption; and further combining lumped nominal information and error feedback to design a controller. The prediction model based hypersonic aircraft Kriging control method has the advantages that design of virtual control variables is not needed, uncertainties of the system are extended from certainties to random distribution by Kriging estimation so as to conform to actual situations more effectively, online parameter adjustment is not needed, the obtained controller is simple and practical in design, and the method is suitable for engineering application.

Description

technical field [0001] The invention relates to a hypersonic aircraft control method, in particular to a hypersonic aircraft Kriging control method 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 in the future need...

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Problems solved by technology

[0008] This method only uses the information of the current moment and the next moment. Due to the uncertainty of the system dynamics parameters, it cannot accurately calculate the future moment information of the virtual control variable, and there is a non-causal problem; and it needs to repeatedly design the virtual control variable, control The device design is complex and difficult to implement

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