基于高旋弹的二维弹道修正技术的研究

【作者】 刘琦；

【导师】 杨新民；

【作者基本信息】 南京理工大学 ， 控制工程（专业学位）， 2019， 硕士

【摘要】 常规弹药制导化是当今武器发展的一个重要方向。弹道修正弹的特点是以较低的成本获得较高的射击精度从而实现对目标的精确压制。其主要作战效能体现在弹药消耗量大幅降低、后勤补给负担减轻、附带毁伤降低,从而缩短了战斗任务完成时间,在有效压制杀伤敌方的同时有利于己方生存。那么如何以较低成本将传统无控弹箭进行制导化改造,提高命中精度,实现精确打击成为国内外当前的研究热点和难点。本文基于气动反旋二维弹道修正弹的控制机理,对高旋二维弹道修正组件(下文简称修正组件)的可控性进行了分析,通过研究修正组件反旋平台在弹丸飞行过程中的可控区域,设计了满足控制要求的反旋平台差动翼的翼展和舵偏角。首先,建立了修正组件反旋平台所受各旋转力矩的数学模型,并建立了可描述反旋平台所受力矩在弹丸飞行过程中变化的弹道模型,以及可描述修正组件控制特性的控制系统模型。其次,对高旋二维弹道修正弹建立物理模型、划分网格、导入CFD仿真软件进行气动仿真。利用压力云图和马赫数云图对二维弹道修正弹和修正组件的反旋平台进行流场分析,并获得所需的气动力系数和气动力矩系数。最后,通过弹道仿真获得不同翼展和舵偏角的反旋平台在弹丸飞行过程中的可控区域,依此设计合理的反旋平台气动外形。并在SIMULINK环境下对修正组件的控制系统进行了仿真。仿真结果表明控制系统响应迅速,可靠性高,动态特性和静态特性良好。更多还原

【Abstract】 In recent years,it is an urgent issue to be solved that how to guide the traditional unmanned projectiles which could improve hit accuracy and achieve the precision strikes.It has become trends of research at home and abroad.And the characteristic of trajectory correction projectile is that the traditional unmanned projectiles can obtain the higher hit accuracy with lower cost,so that it can attack targets accurately.In this paper,a two-dimension high-spinning trajectory correction projectile is regarded as the research object.According to the control principle of the spinning trajectory correction mechanism,the basic conditions of controllable correction mechanism are analyzed.And trajectory and control system model of the projectile are established to simulate.The results are to analyze controllability performance during the flight process comparing with different airfoil shapes of projectile.The main work is as follow:Firstly,the flight mechanics model and control system model of the high-spinning projectile are proposed.The changing of every moment during the flight process with different length of wingspans and different rudder deflection angles can be obtained through trajectory simulation.So,with necessary requirements of moment of the correction mechanism,the most suitable airfoil shape,which has maximum controllable time,can be determined.And a control system that meet the requirement of characteristics is established.Secondly,a numerical simulation was used to obtain aerodynamic parameters of the high-spinning projectile.The result of flow field of the pressure and Mach number can be found.Furthermore,aerodynamic force and aerodynamic moment coefficients are calculated and analyzed.Thirdly,the controllable region of different wingspans and rudder deflections in the process of flight can be calculated through trajectory simulation.And the model of three-closed-loop control system for the correction mechanism is established.A simulation of speed and phase of the two-dimension更多还原