Attitude control method of direct lateral force and aerodynamic composite missile based on hybrid predictive control

A hybrid prediction and attitude control technology, applied in the field of aircraft control, can solve the problems of hybrid and model nonlinear control input, etc.

Active Publication Date: 2016-09-14
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide an attitude control type direct lateral force and aerodynamic compound missile attitude control method to solve the problem that the existing attitude control design method cannot simultaneously solve the problem of model nonlinearity and control input hybrid characteristics

Method used

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  • Attitude control method of direct lateral force and aerodynamic composite missile based on hybrid predictive control
  • Attitude control method of direct lateral force and aerodynamic composite missile based on hybrid predictive control
  • Attitude control method of direct lateral force and aerodynamic composite missile based on hybrid predictive control

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specific Embodiment approach 1

[0040] Specific implementation mode one: combine figure 1 , figure 2 To understand this embodiment, the hybrid predictive control-based attitude control method of direct lateral force and aerodynamic compound missile attitude control method described in this embodiment is realized according to the following steps:

[0041] Step 1. Establish the complete attitude control model and direct lateral force model of the direct lateral force and aerodynamic compound missile, and derive the expression of the direct lateral force in the pitch direction. Through the analysis of the aerodynamic characteristics of the missile body, the nonlinear dynamic model of the missile is Convert to a piecewise affine model;

[0042] Among them, the complete attitude control model process of the established direct lateral force and aerodynamic compound missile is as follows:

[0043] m V · ...

specific Embodiment approach 2

[0061] Specific embodiment two: the difference between this embodiment and specific embodiment one is: the specific process of establishing the direct lateral force model described in step one is:

[0062] The direct lateral force is generated by the attitude control pulse engine group fixedly installed in front of the center of mass of the missile body. There are 180 attitude control pulse engines arranged in dislocation, divided into 10 circles along the longitudinal axis of the missile body, and each circle is surrounded by 18 attitude control pulse engines. Body arrangement; The adjacent attitude control pulse motors in the same circle are spaced at a central angle of 20 °, so that i represents the numbering of the circle, i=1, 2,..., 10, j represents the numbering of the attitude control pulse motors in each circle, j = 1, 2, ..., 18; the distance between the section formed by the connecting line of the nozzle center of the i-th circle attitude control pulse engine and the...

specific Embodiment approach 3

[0072] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is: the specific process of deriving the expression of the direct lateral force in the pitch direction described in step one is:

[0073] The 18 attitude control pulse engines per circle are divided into four ignition control areas: positive and negative pitch control areas and positive and negative yaw control areas, such as Figure 5 shown.

[0074] Since the installation position of each attitude control engine on the missile is fixed, the working cycle is fixed, the number is limited, and it cannot be reused, so a set of specific principles need to be followed when selecting the number, position and firing sequence of the engines. The present invention makes the following assumptions, for each control area, two simultaneous ignitions are allowed at most in each circle, and two simultaneous ignitions are allowed at most, and only attitude control pulse engines in odd ...

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Abstract

The invention relates to an attitude control method of direct lateral force and aerodynamic composite missile attitude control based on hybrid predictive control, which belongs to the field of aircraft control. The invention solves the problem that the existing attitude control design method cannot simultaneously solve the problem of model nonlinearity and control input mixed characteristics. The technical gist of the present invention is: establish the complete attitude control model and the direct lateral force model of direct lateral force and aerodynamic compound missile, and through the analysis of aerodynamic characteristics, transform the nonlinear dynamic model into a segmented affine model; Based on the equivalence between the piecewise affine model and the hybrid logic dynamic model, and considering the hybrid characteristics of the control input, a hybrid logic dynamic model for compound control missiles is established; based on the hybrid logic dynamic model, an explicit model predictive control law is designed to determine the aerodynamic rudder Control law and attitude control engine opening law. The method of the invention is applicable to the field of aircraft guidance and control.

Description

technical field [0001] The invention relates to an attitude control method for an attitude control type direct lateral force and aerodynamic compound missile attitude, in particular to a compound missile attitude control method based on hybrid predictive control, which belongs to the field of aircraft control. Background technique [0002] With the enhancement of the target's maneuverability, in order to achieve effective interception of the target, the missile is required to have a faster overload response speed. Due to the limitation of overload response speed, the traditional pure aerodynamic control missile can no longer meet the requirements of precise interception of high maneuvering targets. The use of direct lateral force and aerodynamic compound control technology is an effective way to improve the response speed of missile overload, but the introduction of direct lateral force makes the design of missile guidance and control system more difficult, which is mainly r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 赵昱宇杨宝庆姚郁贺风华陈松林马杰
Owner HARBIN INST OF TECH
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