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采用三阶活塞理论计算非定常气动力,考虑高超声速下气动加热对扭转刚度的影响,对具有结构迟滞非线性的高超声速二元机翼进行热颤振分析,比较不同厚度比对二元机翼的线颤振速度的影响。研究结果表明:高超声速气动热效应降低了机翼的颤振速度;机翼的厚度比对热颤振速度有较大的影响,热颤振速度随厚度比的增大而增大。高超声速二元机翼的非线性热颤振表现为极限环振荡,通过poincare截面获得机翼响应振幅的分岔图;系统分岔速度小于线颤振速度,极限环振动的幅值随流速的增大而迅速增大。
The third-order piston theory is used to calculate the unsteady aerodynamic forces. Considering the effect of aerodynamic heating on the torsional stiffness at high supersonic speeds, the thermal flutter analysis is performed on the hypersonic binary wing with structural hysteresis nonlinearities. The effect of wing flutter speed. The results show that the hypersonic aerodynamic thermal effect reduces the flutter speed of the wing; the thickness ratio of the wing has a greater influence on the thermal flutter velocity, and the thermal flutter velocity increases with the increase of the thickness ratio. The nonlinear thermal chatter of the hypersonic twin wing shows the limit cycle oscillation, and the bifurcation diagram of the wing response amplitude is obtained through the poincare section. The bifurcation speed of the system is less than that of the line chatter vibration. The amplitude of the limit ring vibration varies with the flow velocity Increase and rapidly increase.