旋转尾翼鸭式布局导弹数值模拟  

Numerical Simulation of a Canard Missile with a Spinning Tail Fin

作　　者：余奇华[1] 敬代勇[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《战术导弹技术》2012年第2期16-19,30,共5页Tactical Missile Technology

摘　　要：通过数值方法求解三维非定常N-S方程组,对旋转尾翼鸭式布局导弹绕流流场进行了数值模拟。研究了时间步长、旋转角速度对导弹气动特性的影响,并比较了与准定常计算结果的差异,重点分析了尾翼旋转的滚转控制特性。数值计算结果表明:尾翼旋转对纵向气动特性影响较小,对横向气动特性影响较大,滚转力矩随转速的增大而增大;尾翼旋转可以有效提高鸭式布局导弹的滚转控制能力。The unsteady N-S equations were solved by numerical simulation to calculate the flow field of a canard missile with a spinning tail fin.The influence of time step,angular velocity of the spinning fin was performed and the differences between steady and unsteady results were also compared.The key issue for the influence of fin spinning to roll control was discussed.The result indicates that the longitudinal force is little affected but the transverse force is more.The roll moment is increased with fin spinning velocity and roll control of a canard missile can be improved by a spinning tail fin.

关 键 词：旋转尾翼 鸭式布局导弹 数值模拟 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]