Linear optimization control method for hypersonic aircraft

Abstract

The invention provides a linear optimization control method for a hypersonic aircraft. The linear optimization control method comprises the following steps that 1, uncertainty of parameters in a mathematical model of the unpowered reentry process of the hypersonic aircraft, unmodeled dynamics and external disturbance are combined together and regarded as total disturbance, and an attitude loop model and an angular speed loop model are established; 2, a linear expansion state observer is designed, output estimation values and total disturbance estimation values of all the loops are obtained; 3,according to the output estimation values and the total disturbance estimation values obtained in the step 2, control input including a total disturbance compensation link and an error feedback control law is designed; and 4, a grey wolf optimization algorithm is adopted to adjust gains of the linear expansion state observer in the step 2 and gains of the error feedback control law in the step 3.According to the linear optimization control method for the hypersonic aircraft, design and parameter optimization of an auto-disturbance-rejection controller of the hypersonic aircraft are achieved,and the dynamic performance, the robust performance and the anti-disturbance performance of the hypersonic aircraft are improved.

Description

technical field [0001] The invention relates to the technical field of hypersonic vehicle control, in particular to a linear optimization control method for a hypersonic vehicle. Background technique [0002] Hypersonic aircraft refers to aircraft, missiles, artillery shells and other winged or wingless aircraft with a flight speed of five times the speed of sound. It has important military status and broad civilian prospects, and is also a research hotspot in the field of aircraft control technology. Hypersonic vehicles have a large flight space, fast speed, long flight distance and high precision requirements, so their structural characteristics, flight characteristics, and dynamic characteristics are more complicated than ordinary aircraft. [0003] The strong nonlinear, strong coupling, fast time-varying, and uncertain characteristics of hypersonic vehicles pose greater challenges to the design of hypersonic vehicle control systems. The traditional PID control is widely...

AI Technical Summary

Problems solved by technology

At present, many scholars have used the ADRC algorithm in the controller design of hypersonic vehicles, and achieved good control results, but most of the ADRC algorithms used for hypersonic vehicles are nonlinear. There are too many parameters, and the adjustment process is complicated. Even if the optimization algorithm is used for parameter adjustment, it is difficult to optimize all parameters.

[0005] In summary, there is an urgent need for a hypersonic vehicle linear optimization control method to solve the problems of too many parameters and difficult tuning in the existing technology, so as to simplify the parameter adjustment process and make the algorithm more suitable for actual flight experiments

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