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Hypersonic flight vehicle attitude control method considering input saturation

A hypersonic and attitude control technology, applied in attitude control, vehicle position/route/height control, non-electric variable control, etc.

Pending Publication Date: 2020-06-16
HUNAN AIRTOPS INTELLIGENT TECH CO LTD
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But the general approximation properties of neural networks / fuzzy systems are only valid on a given bounded closed region

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  • Hypersonic flight vehicle attitude control method considering input saturation
  • Hypersonic flight vehicle attitude control method considering input saturation
  • Hypersonic flight vehicle attitude control method considering input saturation

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Embodiment 1

[0075] A hypersonic aircraft attitude control method considering input saturation, comprising the following steps:

[0076] Step 1: Combine the parameter uncertainty, unmodeled dynamics and external disturbances in the mathematical model of the unpowered reentry process of the hypersonic vehicle into the total disturbance, and establish the mathematical model of the attitude loop and angular rate loop of the hypersonic vehicle , and the mathematical model of each loop is written in a form suitable for the design of the linear ADRC; specifically, the mathematical models of the attitude loop and the angular rate loop are written in a form suitable for the design of the linear ADRC.

[0077] The mathematical model of the unpowered reentry process of a hypersonic vehicle can be written as shown in the following formula (a):

[0078]

[0079] Among them: α, β, μ, γ are the attack angle, sideslip angle, roll angle and track angle of the aircraft respectively; p, q, r are the roll...

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Abstract

The invention provides a hypersonic flight vehicle attitude control method considering input saturation, which comprises the following steps of: 1, combining uncertainty of parameters, unmodeled dynamics and external disturbance in an unpowered reentry process mathematical model of a hypersonic flight vehicle to serve as total disturbance, and establishing models of an attitude loop and an angularrate loop, 2, designing a performance function to constrain steady-state and transient-state performances of state variable tracking errors of the attitude loop and the angular rate loop of the flight vehicle, 3, converting the inequality constraints obtained in the step 2 into equality constraints so as to facilitate controller design, 4, designing a linear extended state observer, and obtainingan output estimation value and a total disturbance estimation value of each loop, and step 5, designing a controller, so that the tracking error of the system can be converged to a preset area underthe condition of facing input saturation constraints. According to the method, the design and parameter optimization of the linear active disturbance rejection controller of the hypersonic flight vehicle are realized, and the dynamic performance, the robust performance and the anti-interference performance of the hypersonic flight vehicle are improved.

Description

technical field [0001] The invention relates to the technical field of hypersonic vehicle control, in particular to an attitude control method of a hypersonic vehicle considering input saturation. 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...

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/101
Inventor 罗世彬吴瑕
Owner HUNAN AIRTOPS INTELLIGENT TECH CO LTD
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