有翼导弹动态气动特性数值研究

为准确预测飞行器的机动特性,故开展其动态气动特性研究.应用非结构动网格技术建立了可模拟飞行器作周期性俯仰运动的强迫振荡法.选取NACA 0012翼型为研究对象对该方法进行验证,进而计算了有翼导弹Finner在各马赫数下的静、动导数,并分析了Finner导弹在不同减缩频率下的动态气动迟滞特性.结果表明,文中方法能够有效模拟有翼导弹在不同马赫数下的动态气动特性,结果正确可靠,具有较高的工程应用价值.

Research on Numerical Virtual Flight of Spinning Projectile

In order to suppress or eliminate gyro instability to improve the flight stability and hit accuracy of spinning projectile,the numerical simulation of virtual flight of M852 projectile and Basic Finner missile model was carried out by using coupled URANS equation and rigid motion equations.The computation results fitted well with the test results.Different initial yaw angle had little effect on the pitching / yaw cycle of M852 bullet,but the larger the initial yaw angle was,the larger the motion amplitude,and the larger the lateral deviation,the faster the speed decreased.For Basic Finner model with low-speed rotation,the flight characteristics of different emission velocities were different,and it was embodied in the aspect of velocity evolution,displacement fluctuation and cone amplitude,etc..