某型导弹动导数风洞试验和CFD数值模拟  

Wind Tunnel Test and CFD Numerical Simulation of Dynamic Derivative for a Certain Type of Missile

作　　者：岑梦希 张瑞民[1,2] Cen Mengxi;Zhang Ruimin(Caihong UAV Technology Limited Company,China Academy of Aerospace Aerodynamics,Beijing 100074,China;No. 2 Research Institute,China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院彩虹无人机科技有限公司,北京100074 [2]中国航天空气动力技术研究院第二研究所,北京100074

出　　处：《航空工程进展》2019年第3期371-375,共5页Advances in Aeronautical Science and Engineering

摘　　要：动导数的精确预测对于弹箭类武器的成功研制至关重要。以某型导弹动态特性的研究为对象,在FD06风洞中采用自由振动法完成动态特性试验,获取该型导弹俯仰和滚转两个方向的典型振幅衰减曲线和动导数结果;针对该型导弹,基于双时间推进法数值求解非定常N-S方程和强迫运动方程,获取该型导弹俯仰动导数和滚转动导数。结果表明:CFD计算结果与风洞试验结果有较好的一致性;在给定马赫数和攻角下CFD数值模拟结果可以为后续工程型号研制提供参考。The accurate prediction of dynamic derivative is of significant importance for the successful development of missile weapons.Taking the dynamic performance of a certain missile as research subject,the free vibration method is used in FD06 wind tunnel to accomplish the dynamic performance experiment,and get the typical decay curves of amplitude and dynamic derivatives in pitching and rolling directions.On the basis of dual time-stepping approach,the unsteady N-S equation and forced movement equation are solved by numerical value,which can obtain the pitching and rolling dynamic derivatives of the missile.The results show that the CFD numerical simulation results are in accordance with wind-tunnel test data,which can provide a reference for the following engineering model development in a certain range of Mach numbers and angles of attack.

关 键 词：动稳定 俯仰动导数 滚转动导数 风洞试验 CFD数值模拟 

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]