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通过数值模拟探索了一种运用充气气囊抑制双垂尾抖振的新方法。该文方法利用充气气囊可迅速充气变形的特点,在三角翼上翼面靠近顶点沿涡核的位置设置气囊。在小迎角下气囊不凸起,从而保证机翼前缘涡的强度以产生非线性涡升力;当大迎角抖振现象较严重时,迅速对气囊充气形成凸起,该凸起通过对前缘分离涡的强度和涡空间位置的影响,减弱涡破裂对双垂尾的非定常气动载荷激励,达到抑制抖振的目的。对某三角翼双垂尾布局模型的计算结果表明:气囊可以使前缘涡的涡核弯曲、扭转,减弱了前缘涡的强度,使前缘涡破裂点位置提前,在大迎角范围可将垂尾绕翼根的弯矩值显著减小,并且减小了垂尾表面压力脉动的幅度和对应的功率谱密度的峰值。因此,该文所探索的利用充气气囊抑制抖振的方法是一种简单可靠,并且值得进一步研究的技术途径。
A new method of suppressing double vertical tail chattering using inflatable airbag was explored by numerical simulation. The method utilizes the characteristic that the inflatable balloon can be rapidly inflated and deformed, and the airbag is arranged along the vortex core near the apex of the delta wing. The airbag does not protrude at a small angle of attack, thus ensuring the strength of the leading edge vortex to generate non-linear eddy force. When the chattering phenomenon is severe at a high angle of attack, the airbag is quickly inflated to form a bulge, The strength of the leading edge separation vortex and the position of the vortex space, and weakening the unsteady aerodynamic load excitation of the vortex rupture to the double vertical tail, so as to suppress the vibration. The calculation results of a double-tail layout model for a delta wing show that the airbag can bend and twist the vortex nucleus of the leading edge vortex and weaken the strength of the leading edge vortex so that the position of the leading vortex rupture point is advanced, The bending moment around the root of the tail is significantly reduced, and the amplitude of the pressure pulsation at the vertical tail surface and the peak of the corresponding power spectral density are reduced. Therefore, this paper explores the use of inflatable airbags to suppress chatter vibration method is a simple and reliable, and worthy of further study of the technical approach.