基于大指令变化率下的防空导弹姿态控制方法

doi:10.12305/j.issn.1001-506X.2024.07.28

Abstract

Abstract:

Aiming at the problem of poor attitude control quality caused by strong target maneuverability of air defense missile, an event-triggered control method is proposed. Firstly, the unknown command change rate caused by the strong maneuverability of the target and the reason of the large steady-state error caused by the excessive command change rate are analyzed. To solve this problem, a nonlinear fastest tracking differentiator is introduced to obtain the command change rate, the relationship between the command change rate and the attitude angle error is studied, the steady-state effect index is defined, and the new event-based control quantity is designed based on this index. By using sliding mode control and disturbance observer, the steady-state error of the system is suppressed within 5% error band under the condition of higher command change rate. In the background of engineering practice, the numerical simulation takes into account the deviation of aerodynamic parameters and the limiting of actuator, and the simulation results verify the effectiveness of the designed control system.

Key words: air defense missile, attitude control, trigger control, differentiator, steady-state effect index

CLC Number:

V448.2

Shuaihao YAN, Mingying WEI, Yongbin ZHENG. Attitude control method of air defense missile based on large command change rate[J]. Systems Engineering and Electronics, 2024, 46(7): 2465-2474.

Figures/Tables 14

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Table 1

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参数	取值
姿态角指令	$\left\{\begin{array}{l}\alpha_{c}=7 \sin (4 {\rm{\mathsf{π}}} t)^{\circ} \\\beta_{c}=0^{\circ} \\\gamma_{c}=0.2^{\circ}\end{array}\right.$
观测器参数	$\boldsymbol{\varLambda}=\operatorname{diag}(50, 50, 50, 50, 50, 50)$
TD	r=200, α=0.75
控制系统参数	$\left\{\begin{array}{l}\boldsymbol{K}_{1}=\operatorname{diag}(50, 50, 50) \\\boldsymbol{K}_{2}=\operatorname{diag}(5, 10, 5)\end{array}\right.$ $\left\{\begin{array}{l}\boldsymbol{M}_{1}=\operatorname{diag}(0.01, 0.01, 0.001) \\\mathbf{N}_{1}=\operatorname{diag}(0.001, 0.001, 0.0001)\end{array}\right.$ $\left\{\begin{array}{l}\boldsymbol{M}_{2}=\operatorname{diag}(0.01, 0.1, 0.1) \\\mathbf{N}_{1}=\operatorname{diag}(0.001, 0.01, 0.01)\end{array}\right.$ $\left\{\begin{array}{l}J_{i}>0, k_{0 i}=-0.9 \\J_{i}<0, k_{0 i}=1.1\end{array}\right.$

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Attitude control method of air defense missile based on large command change rate

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