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通过试验方法分析了三角翼前缘分离涡与垂尾抖振之间的关系,深入研究了尾迹流动对垂尾抖振各阶模态的激励作用。计算得到了垂尾模型固有频率及各阶模态。在风洞试验中,应用激光片光烟流场显示技术,得到了三角翼模型在风速为30m/s下,各迎角的涡结构;使用加速度传感器测量了垂尾翼根和翼梢的抖振响应;使用热线风速仪测量了垂尾翼根和翼梢位置的脉动速度分量。结果表明:前缘涡破裂后产生的高湍流度的尾迹是垂尾抖振的直接原因,抖振边界与涡破裂的强度和位置有关;涡破裂后尾迹与垂尾产生共振,使得抖振加速度响应频率与垂尾固有频率一致;涡破裂后,在较小迎角下,尾迹对垂尾的高频振动模态的激励较为明显,在较大迎角下,涡破裂流动对垂尾低频振动模态的激励加强了。
The relationship between the separation vortex and the vertical tail chattering vibration of the delta wing front wing is analyzed by the test method. The excitation of each wake mode chattering vibration is further studied. The natural frequency and mode of vertical tail model are calculated. In the wind tunnel test, the vortex structure of the delta wing model at each angle of attack is obtained by using the laser light flare flow field display technology. The chatter vibration of the vertical tail wing and wing tip is measured by the acceleration sensor Response; Hot-wire anemometer was used to measure the pulsating velocity components at the root and the tip of the tail. The results show that the wake of high turbulence generated by the vortex rupture is the direct cause of vertical chattering. The chattering boundary is related to the strength and location of vortex rupture. The wake and vertical tail resonate so that the chattering acceleration The response frequency is consistent with the natural frequency of vertical tail. After the rupture of the vortex, the wake excited the high-frequency vibration mode of the vertical tail at a smaller angle of attack. At the higher angle of attack, Modal incentives have been strengthened.