气动外形对火箭弹弹道特性影响的数值模拟研究  

Numerical Simulation Research on Effect of Aerodynamic Configuration on Rocket Projectile's Ballistics Characteristics

作　　者：徐永杰[1] 王志军[1] 吴国东[1] 尹建平[1] 董方栋 XU Yongjie;WANG Zhijun;WU Guodong;YIN Jianping;DONG Fangdong(School of Mechatronics Engineering,North University of China,Taiyuan 030051,China;No.208 Research Institute of China Ordnance Industries,Beijing 102202,China)

机构地区：[1]中北大学机电工程学院,太原030051 [2]中国兵器工业第208研究所,北京102202

出　　处：《弹箭与制导学报》2018年第4期11-14,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：瞬态冲击技术重点实验室基金(61426060101);国家自然科学基金(11572291)资助

摘　　要：为了研究火箭弹气动外形对弹道特性的影响,设计了不同气动外形的火箭弹模型;利用ANSYS FLUENT对不同火箭弹模型飞行流场进行数值模拟,获得其气动特性参数;建立质点弹道模型,利用已经获得的气动力参数进行外弹道仿真,分析气动外形对火箭弹射程的影响。结果表明,经过优化设计的火箭弹模型可以提供0.08～164.53 m的射程变化量。研究结果可以为火箭弹气动布局优化设计及其工程应用提供理论和技术支持。In order to study the effect of rocket projectile’s aerodynamic configuration on its ballistic characteristics, rocket projectile models with different aerodynamic configuration were designed. Flow field numerical simulation was conducted for rocket projectile models under different Mach number flying condition by ANSYS FLUENT and the aerodynamic characteristic parameters were obtained for each rocket projectile model. For analyzing the effect of aerodynamic configuration on fire range, a particle trajectory model is established for trajectory simulation using the aerodynamic characteristic parameters obtained. Results show that the firing range change within 0.08-164.53 m can be provided by the optimized rocket projectile models. Research results can provide theoretical and technical support for rocket projectile’s aerodynamic configuration optimization design and its engineering application.

关 键 词：气动外形 火箭弹 弹道特性 数值模拟 

分 类 号：TJ410.3[兵器科学与技术—火炮、自动武器与弹药工程]