A Linear Optimal Control Method for Hypersonic Vehicle

Abstract

The present invention provides a hypersonic vehicle linear optimization control method, comprising the following steps: Step 1: combining the uncertainty of the parameters in the mathematical model of the unpowered reentry process of the hypersonic vehicle, unmodeled dynamics and external disturbances To generate the total disturbance, establish the model of the attitude loop and the angular rate loop; Step 2: Design a linear expansion state observer to obtain the estimated output value of each loop and the estimated value of the total disturbance; Step 3: According to the estimated output value and the total estimated value obtained in Step 2 Disturbance estimation value, design control input including the total disturbance compensation link and error feedback control law; Step 4: Using the gray wolf optimization algorithm, the gain of the linearly extended state observer and the gain of the error feedback control law in step 2 and step 3 are calculated set. The invention realizes the design and parameter optimization of the linear active disturbance rejection controller of the hypersonic aircraft, and improves the dynamic performance, robust performance and anti-interference performance of the hypersonic aircraft.

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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