无人机导弹滑弹一体式发射对机翼的气动干扰  

The UAV Airfoil Aerodynamic Interference of Missile Launched from Rail-catapult Integrated Launcher

作　　者：王博[1] 马贵春[1] 陈阳[1] 董浩[1] 

机构地区：[1]中北大学机电工程学院,太原030051

出　　处：《弹箭与制导学报》2016年第2期111-114,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：无人机机载导弹发射产生的尾喷流对机翼的气动干扰影响载机飞行安全。本研究以Fluent软件为基础,采用二维非结构动网格技术并选择标准k-ω二方程湍流模型,对导弹沿导轨弹射滑行后点火和直接点火的发射过程分别进行数值模拟,并对两组结果进行对比。结果表明:滑弹一体式发射装置在一定程度上降低导弹尾喷流对机翼的气动影响。该研究为无人机导弹滑弹一体式发射装置的研究提供一定参考。When airborne missile launched from UAV, its exhaust jet has an impact on UAV airfoil and safety. This study is based on two-dimensional unstructured dynamic grids and standard k-omega tow-equation turbulence model of the software Fluent. In this research differ-ence between missile ignition firing and ignition firing after ejection was analyzed, and these two results were compared. The results show that the rail-catapult integrated launcher can reduce aerodynamic influence on airfoil caused by missile exhaust jet stream. The results will provide certain reference for research of rail-catapult integrated missile launcher of UAV.

关 键 词：无人机 导弹发射 尾喷流 非结构动网格 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]