Flutter suppression concept is demonstrated by performin wind-tunnel tests in a low subsonic flow regime. The wing model, witha trailing edge control surface, is constructed to have a bending-torsion flutter. The control surface is actuated by a flexure-hinged lead zirconate titanate stack mechanism acting as an aerodynamic effector. The flutter experiments are conducted using a digital controller, implemented in dSPACE DS1104, keeping the wing model at 4 deg angle of attack. The wing response is measured by lead zirconate titanate sensors, which are used to generate the feedback control to vibrate the control surface in antiphase motion with respect to the main surface to introduce active aerodynamic control. It is noticed that both bending and torsion modes are stabilized in dosed-loop configurations. The damping trend of the flutter mode shows an expanded flutter envelope that is estimated to be around 20%. The actuators are operated within 1000 V/mm, though their allowable field13; strength is 1500 V/ mm.
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机译：颤振抑制的概念已通过在低亚音速流态下进行风洞测试得到了证明。带有后缘控制面的机翼模型构造为具有弯曲扭转颤振。控制面由可弯曲铰接的钛酸锆钛酸铅叠层机构驱动，用作空气动力学效应器。颤振实验是使用在dSPACE DS1104中实现的数字控制器进行的，将机翼模型的迎角保持在4度。机翼响应由锆钛酸铅传感器测量，该传感器用于生成反馈控制，使控制面相对于主面发生反相运动，从而引入主动的空气动力控制。注意到弯曲和扭转模式在剂量环构造中都是稳定的。颤振模式的阻尼趋势显示颤振包络扩展，估计约为20％。尽管执行器允许的磁场范围为13，但它们在1000 V / mm的范围内运行；强度为1500 V / mm。
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