带微型扰流片的尾翼弹飞行弹道仿真  

Trajectory Simulation of Fin Stabilized Projectile with Micro Spoilers

作　　者：刘凯[1] 常思江[1] 张华[1] 

机构地区：[1]南京理工大学能源与动力工程学院,南京210094

出　　处：《兵器装备工程学报》2016年第12期1-6,共6页Journal of Ordnance Equipment Engineering

基　　金：中国博士后科学基金(2013M541676);国家自然科学基金项目(11402117)

摘　　要：为了研究微型扰流片的控制机理及控制效果,以某带微型扰流片的尾翼弹为研究对象,从动力学角度分析微型扰流片动作对尾翼弹飞行弹道的影响,建立了该类弹箭的六自由度飞行动力学模型并进行了飞行弹道数值仿真;不同速度条件下扰流片对弹箭侧偏和射程的修正结果表明:在弹箭飞行过程中某一个时刻启动微型扰流片后,弹箭的飞行姿态可以发生较大的变化,从而改变其飞行轨迹,达到弹道修正的目的。A standard 6-degree-freedom aerodynamic based on the fin-stabilized projectile with micro-spoilers model was established and trajectory-stimulated and the influence on the projectile of it by the performances of micro spoilers were analyzed from the perspective by dynamics in order to do research on the controlling principle and effect of micro spoilers. According to the modified result lateral deviation and range made by micro-spoilers on the projectile at different speeds, the flight attitude of projectile can be greatly changed when the micro spoilers are opened at a point of flight, so that the flight profile can be altered thus to meet the aim of correcting ballistic trajectory.

关 键 词：弹道模型 弹道仿真 尾翼弹 微型扰流片 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]