Speed control modeling method of cruise missile

A speed control and cruise missile technology, applied in the field of control, can solve the problems of strong speed control constraints and difficulty, and achieve the effect of improving modeling accuracy

Active Publication Date: 2016-11-16
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0004] The thrust performance of a cruise missile is closely related to the flight state, missile attitude, and flight environment, so its speed control has strong constraints and is difficult

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  • Speed control modeling method of cruise missile
  • Speed control modeling method of cruise missile
  • Speed control modeling method of cruise missile

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Embodiment Construction

[0023] The technical solution of the present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments. Apparently, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts belong to the protection scope of the present invention.

[0024] First, the modeling of the ramjet is carried out. Considering that the ramjet is a small closed-loop control system, its dynamic characteristics cannot be ignored. The ramjet model is described by two parts, the static model and the dynamic model, such as figure 1 shown. The static model refers to the steady-state thrust performance and static pressure margin under different flow states and gas flow rates (or residual gas coefficients), expressed in the form of an interpolation table. The dyn...

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Abstract

The invention brings forward a speed control modeling method of a cruise missile. Through combination with a description of dynamic features of a ramjet engine, a composition and modeling flow of a speed control loop is given. The method specifically comprises modeling of the ramjet engine, a speed loop total model for simulation and a small-disturbance model for control. A foundation is laid for performance evaluation of the cruise missile and design of a controller. The speed control loop modeling method for simulation, brought forward by the invention, effectively reflects interface relations among a projectile body, the ramjet engine, atmosphere environment, a measurement apparatus and the controller, and provides a basis for realizing engine performance and total performance evaluation and technical indexes. The small-disturbance model modeling method for control, provided by the invention provides a reasonable design model for the design of a speed controller and can effectively improve the control quality.

Description

technical field [0001] The invention belongs to the technical field of control, and in particular relates to a speed control modeling method of an air-breathing cruise missile. Background technique [0002] Cruise missiles are powered by ramjet engines, which have the advantages of high specific impulse and continuously adjustable thrust, which makes it possible to precisely control the speed, thus meeting the requirements of various flight missions. [0003] The speed control of traditional missiles is achieved by adjusting the angle of attack through rudder deflection, and the angle of attack profile is constrained by the trajectory, so precise speed control cannot be achieved. Compared with traditional missiles, cruise missiles have an additional one-dimensional control variable. The thrust is adjusted through the gas flow (or residual gas coefficient), and the angle of attack is adjusted through the rudder deflection. And tasks such as deceleration and pressure attack. ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 宋少倩陈新民尹立中陈世立雷延花韩英宏陈松卢鑫李新田刘珺怡温玉芬陈皓高晶晶高庆金红新佟泽友谢晓阳刘宁赵君伟
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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