基于Matlab/Simulink的小型制导炮弹六自由度运动仿真
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摘要
介绍了以小型制导炮弹为研究对象,提出一种基于Matlab/Simulink的炮弹六自由度运动仿真的新方法,主要适用于射程短、口径小、控制通道简易的制导炮弹。这种方法主要采用一种系统模块化的建模思想,建立了一种制导炮弹的六自由度运动模型和空气动力学模型,然后对各个子模块分别采用Simulink建立单元仿真模型,最终通过对单元仿真模型的集成得到了制导炮弹的六自由度仿真模型。通过对模型的仿真,不仅验证了数学建模的正确性,而且可以表明该模型能够正确地反应制导炮弹的弹道特性。相对以往针对导弹的建模方法,它具有简单快捷、编程简化、运行速度快、调试方便等优点。
Taking small guilding shell as the research object,a new method of shells of six degrees of freedom movement simulation based on Matlab/Simulink is put forward,mainly suitable for the short range,small diameter and simple control channelguidance ammunition. This method mainly adopts a system of modular modeling idea,sets up a kind of guided projectile of six degrees of freedom movement model and aerodynamic model,and then each module unit simulation model is established by using Simulink,finally,by integrating unit simulation model of,the guidance projectile of six degrees of freedom simulation model is obtained. The simulation of the model not only verifies the correctness of mathematical modeling,but also indicates that the model can accurately reflect the ballistic characteristics of the guided projectile. Compared with previous modeling methods for missiles,it has the advantages of simple and fast programming,fast operation speed and convenient debugging.
Taking small guilding shell as the research object,a new method of shells of six degrees of freedom movement simulation based on Matlab/Simulink is put forward,mainly suitable for the short range,small diameter and simple control channelguidance ammunition. This method mainly adopts a system of modular modeling idea,sets up a kind of guided projectile of six degrees of freedom movement model and aerodynamic model,and then each module unit simulation model is established by using Simulink,finally,by integrating unit simulation model of,the guidance projectile of six degrees of freedom simulation model is obtained. The simulation of the model not only verifies the correctness of mathematical modeling,but also indicates that the model can accurately reflect the ballistic characteristics of the guided projectile. Compared with previous modeling methods for missiles,it has the advantages of simple and fast programming,fast operation speed and convenient debugging.
引文
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[15]张江华,裴阿平.制导炮弹六自由度建模仿真[J].火控雷达技术,2011(1):5-8.
[2]黄鸿鑫.迫击炮弹的特点及发展趋势[J].科技展望,2017(1):24-28.
[3]史金光,王中原,易文俊.滑翔增程弹方案弹道特性的研究[J].弹道学报,2003(15):51-54.
[4]侯明,戴学谦,毕嗣民.视频制导炮弹下滑段攻角及其对制导修正的影响研究[J].中国设备工程,2016,(18):172-173.
[5]曹菲,杨小冈,缪栋.景象匹配制导基准图选定准则研究[J].计算机应用研究,2005,22(5):137-139.
[6]朱少雄,施冬梅.制导迫击炮弹发展现状及关键技术[J].飞航导弹,2016(4):67-70.
[7]徐秋坪,常思江,王中原.滑翔制导炮弹非线性自抗扰过载控制器设计[J].兵工学报,2017,38(7):1273-1281.
[8]王强,石丽娜,严慎武,等.国外末制导弹药的发展与研究[J].飞航导弹,2013(4):55-60.
[9]赵乐.自旋制导炮弹自适应解耦控制方法研究[D].南京:南京理工大学,2017.
[10]Liang,Zheng,Huang,et al.Optimal design of the aero-dynamic parameters for a supersonic two-dimensionalguided artillery projectile[J].Defence Technology,2017,13.
[11]Courtney E,Courtney A,Courtney M.ExperimentalTests of the Proportionality of Aerodynamic Drag to AirDensity for Supersonic Projectiles[J].Physics,2015,11.
[12]Wang Y,Song W D,Fang D,et al.Guidance and Con-trol Design for a Class of Spin-Stabilized Projectiles witha Two-Dimensional Trajectory Correction Fuze[J].In-ternational Journal of Aerospace Engineering,2015,(5):1-15.
[13]Li J M,He G L,Guo H Y.A Study on the AerodynamicCharacteristics for a Two-Dimensional Trajectory Correc-tion Fuze[J].Applied Mechanics&Materials,2015,(16):370-375.
[14]左鹏峰.基于MATLAB环境的末制导炮弹制导系统半实物仿真[D].南京:南京理工大学,2006.
[15]张江华,裴阿平.制导炮弹六自由度建模仿真[J].火控雷达技术,2011(1):5-8.