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ANSYSFLUENT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0.08~164.53m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.