无人机机载导弹分离轨迹的数值仿真  

Numerical Simulation of Trajectory of Missile Separated from UAV

作　　者：沈琼[1] 余雄庆[1] 

机构地区：[1]南京航空航天大学飞行器先进设计技术国防重点学科实验室,南京210016

出　　处：《弹箭与制导学报》2009年第5期99-102,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：载机发射导弹时,对导弹流场有复杂干扰,进而影响导弹在发射初始阶段的姿态和运动轨迹。为模拟导弹从载机分离后的气动特性和相对运动,文中应用CFD商用软件CFD-FASTRAN,采用动态嵌套网格技术,基于Euler方程并耦合该软件的刚体六自由度(6-DOF)运动模块求解导弹发射时的非定常流场及运动轨迹。分析挂架弹射力和载机迎角变化对分离过程运动参数的影响,发现挂架弹射力仅是加快了导弹的运动,而迎角的变化对导弹运动参数有较大影响。研究结果对飞机上如何布置外挂导弹具有参考价值。The low-field is disturbed when a missile is launched from aircraft, which influences initial attitude and trajectory of the launched missile. To simulate trajectory of the missile separated from aircraft, the CFD software named CFD-FASTRAN was used to compute the unsteady flow-field and the missile trajectory by using the moving chimera grid, Euler equations and six degree-of-freedom equation. The effect of launching force and angle of attack on the missile trajectory was presented, it is indicated that launching force just accelerates the movement of the missiles while the angle of attack change have a greater impact on movement parameters of the missile. The simulation results can provide guidance for the layout of missile in aircraft design.

关 键 词：机载导弹 飞机发射装置 运动轨迹 分离 动态嵌套网格 六自由度方程 

分 类 号：TJ768[兵器科学与技术—武器系统与运用工程] V279[航空宇航科学与技术—飞行器设计]