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Frequency and time domain flutter computations of a wing with oscillating control surface including shock interference effects

机译：具有振动控制面的机翼的频域和时域颤动计算，包括冲击干扰效应

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In this study, the nonlinear aeroelastic characteristics of a wing with an oscillating control surface have been examined in transonic and supersonic regimes. The various effects of rotational stiffness on flutter have also been observed. A modified transonic small-disturbance (TSD) theory is used to more effectively analyze the unsteady aerodynamics of a wing with an oscillating control surface. In the flutter analysis, a coupled time integration method (CTIM) and a transient pulse method (TPM) were used to examine the effects of rotational stiffness reduction on the control surface. The present study shows that the severe decrease of flutter speed and the flutter mode transition can be induced by the reduction of rotational stiffness. In particular, it is shown that the aerodynamic effects of control surface oscillation play an important role in this flutter speed reduction.
机译：在这项研究中，已经在跨音速和超音速状态下检查了具有振动控制面的机翼的非线性气动弹性特征。还已经观察到旋转刚度对颤振的各种影响。改进的跨音速小扰动（TSD）理论用于更有效地分析具有摆动控制面的机翼的非定常空气动力学特性。在颤动分析中，使用耦合时间积分法（CTIM）和瞬态脉冲法（TPM）来检查旋转刚度降低对控制面的影响。本研究表明，旋转刚度的降低可以引起振颤速度的严重降低和振颤模式的转变。特别地，表明控制表面振动的空气动力学作用在该扑扑速度降低中起重要作用。

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