多片弹翼反坦克导弹动导数数值计算  

Numerical Compution of the Dynamic Derivatives of a Multi-wing Antitank Missile

作　　者：岳杰顺 吴颂平[1,2] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100091 [2]北京航空航天大学国家计算流体力学实验室,北京100091

出　　处：《兵工学报》2016年第2期367-372,共6页Acta Armamentarii

基　　金：国家自然科学基金项目(61378077)

摘　　要：为估计一种多片弹翼反坦克导弹动态气动特性,改进现有的数值模拟计算飞行器动导数的方法。采用准定常方法,利用滑移网格技术模拟飞行器定常滚转运动流场。使用减缩频率法,通过更改来流条件,模拟飞行器的非定常俯仰振荡运动。在此基础上介绍了滚转、俯仰阻尼力矩的具体计算过程。将这些方法应用于标准验证模型和一种多翼反坦克导弹的动导数计算中。计算结果表明:用这些计算方法计算飞行器的动导数,具有精度高、效率高的特点,可以被工程应用所参考。The methods of computing the dynamic derivatives are improved to estimate the unsteady aerodynamic characteristics of a multi-wing antitank missile. A quasi-steady state method is applied in computing the roll damping coefficient. The steady state flow is simulated by using sliding mesh technology.The unsteady pitch movement is simulated by using a reduced frequency method. In the movement,a far field velocity boundary condition is forced to oscillate. The computing procedures of roll and pitch damping moments are introduced based on these methods. These methods are applied to predict the dynamic derivatives of standard calibration model and a multi-wing antitank missile. The results indicate that the improved methods described have high accuracy and efficiency for the calculation of dynamic derivatives.And the improved methods are available for engineering applications.

关 键 词：兵器科学与技术 动导数 滚转 非定常俯仰 阻尼力矩 多翼反坦克导弹 

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]