无伞末敏子弹大攻角非线性空气动力和力矩模型  

Non-linear Aerodynamic Force and Moment Model for Non-parachute Terminal Sensitive Sub-ammunition at Large Angle of Attack

作　　者：舒敬荣 叶结松[1] 郝延军[1] 张婷 

机构地区：[1]陆军军官学院,合肥230031

出　　处：《火力与指挥控制》2015年第6期21-25,共5页Fire Control & Command Control

基　　金：国家自然科学基金(11272356);中国博士后科学基金资助项目(2012M521842)

摘　　要：以无伞末敏子弹为背景,分析了描述大攻角飞行弹丸横向运动和角运动的运动变量,建立了大攻角情况下弹丸所受非线性空气动力和空气动力矩的模型,推导出了复数形式的弹丸横向运动与角运动方程。数值积分计算表明,弹丸在特定非线性空气动力和力矩作用下,能够形成所需形式的扫描运动,证明所建力学模型正确合理,可以用于无伞末敏子弹动力学特性的分析与计算。Against the background of non-parachute terminal sensitive sub-ammunition,the variables which describes the projectile＇s lateral and angular motion at large angle of attack are analyzed,the non-linear aerodynamic force and moment model at large angle of attack is set up,and the projectile＇s lateral and angular motion equation in complex number form is deduced. Numerical integration calculation shows that the projectile can form the required scanning motion under the action of given non-linear aerodynamic force and moment,which demonstrate that the established mechanical model is correct and reasonable,and can be used in non-parachute terminal sensitive sub-ammunition＇s dynamic characteristics analysis and calculation.

关 键 词：外弹道学 飞行力学 末敏弹 大攻角 非线性空气动力 

分 类 号：TJ012.3[兵器科学与技术—兵器发射理论与技术] TJ410.1