Time scale function decomposition based hypersonic aircraft actuator saturation control method

Abstract

The invention discloses a time scale function decomposition based hypersonic aircraft actuator saturation control method. The method is used for solving the technical problem of difficulty in engineering realization under the existing hypersonic aircraft actuator saturation condition. The method includes: obtaining a high-speed slow variable subsystem, a speed slow variable subsystem and an attitude fast variable subsystem by time scale decomposition, and building a discrete form of an original system through an Eulerian method; regarding the height and the speed in a fast subsystem design process as constants so as to achieve model simplification; considering actuator saturation limitations, and importing auxiliary control variables to design throttling valve openness and the controlpiston deflexion angle; and designing an updating law of a neural network by importing an auxiliary error variable. The time scale function decomposition based hypersonic aircraft actuator saturation control method has the advantages that computer control characteristics are combined, a discrete model is built, the subsystems are designed according to time scale function decomposition, the actuator saturation condition is fully considered during controller 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 actuator saturation control method based on time scale function decomposition, 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] "Nonlinear Control of An Uncertain Hypersonic Aircraft Model Using Robust Sum-of-squares Method" (Ataei, A., Wang, Q., "IET Control Theory & Applications", Volume...

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Problems solved by technology

[0004] "Adaptive Discrete-time Controller Design with Neural Network for Hypersonic Flight Vehicle via Back-stepping" (Xu Bin, Sun Fuchun, Yang Chengguang, Gao Daoxiang, Ren Jianxin, "International Journal of Control...

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