Hypersonic aerocraft Kriging control method based on equivalent model

Abstract

The invention discloses a hypersonic aerocraft Kriging control method based on an equivalent model and belongs to the field of control over aerocrafts, and the method is used for solving the technical problem that the discrete adaptive control of an existing hypersonic aerocraft has difficulty in being realized in an engineering manner. The method comprises the following steps of: firstly converting a height subsystem model of a hypersonic aerocraft into a strict feedback form, and then establishing a discrete strict feedback form of an original system through an eulerian method; and considering the causal relationship of the system and establishing the equivalent model of the original system. The equivalent model can be used for making full use of future output and analyzing historical information of systematic uncertainty; the systematic uncertainty is popularized to a random field by utilizing a Kriging method, and better conforms to the actual condition, the constructivity predication can be carried out, online self-adapting adjustment on parameters is not required, and the method is convenient to implement; by virtue of nominal feedback and error feedback, a controller is designed according to a contragradience method strategy; the controller obtained by virtue of combination of the characteristics of computer control and model conversion can be used for effectively solving the non-causal problem; and the method is suitable for technical 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 an equivalent 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] At present, the control of hypersonic aircraft is mostly concentrated in the continuous domain; with the development of computer technology, the control system of hypersonic aircraft in th...

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Problems solved by technology

[0007] This method only uses the information of the current moment and the next moment. Due to the uncertainty of the system dynamic parameters, it is impossible to accurately calculate the future moment information of the virtual control quantity. There is a non-causal problem, which is difficult to realize in engineering.

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