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利用非定常流场数值计算方法模拟飞行器强迫俯仰振荡仅能得到俯仰力矩系数对迎角变化率和俯仰角速度的动导数之和,而动稳定性分析需要单独的动导数数值.为解决这个问题,利用滑移网格模拟强迫振荡运动,得到俯仰力矩系数对迎角变化率和俯仰角速度的动导数之和.利用旋转参考坐标系模拟定常拉升,得到俯仰力矩系数对俯仰角速度的动导数.利用旋转参考坐标系模拟匀速滚转,得到滚转力矩系数对滚转角速度的动导数.对有翼导弹和水上飞机进行了纵向和横向动导数的计算.计算结果与试验数据、文献数据以及其他方法得到的结果具有较好的一致性,表明提出的方法可用于复杂外形飞行器动导数计算.
Using unsteady flow field numerical simulation to simulate the forced pitch oscillation of the aircraft can only get the sum of the dynamic derivative of the pitch moment coefficient to the angle of attack change rate and the pitch angular velocity. However, the dynamic stability analysis needs a separate dynamic derivative value. To solve this problem, The slip-grid is used to simulate the forced oscillation motion, and the sum of the dynamic derivatives of the pitch moment coefficient and the pitch angle angular rate is obtained.The dynamic derivative of the pitch moment coefficient to the pitch angular velocity is obtained by using the rotating reference coordinate system to simulate the steady- The rotating reference frame simulates the uniform roll, and obtains the dynamic derivative of the rolling moment coefficient to the roll angular velocity. The calculation of the longitudinal and transverse dynamic derivatives of the winged missile and the seaplane is carried out. The calculation results, the experimental data, the literature data and other methods The obtained results are in good agreement, indicating that the proposed method can be used to calculate the dynamic derivatives of complex profiled aircraft.