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Application of piezoelectric actuators for vibration reduction in the F-15.

机译：压电执行器在F-15中的减振应用。

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Buffet excitation on the F-15 aircraft at high angles of attack reduces the life cycle of the vertical tails and the readiness of the aircraft. Previous studies have demonstrated a reduction on vibration to up to 50% with the application of active control systems to the twin tail structure of the F-15.; This study applies the concept of noise cancellation in vibrating structures. A 4.7% scaled F-15 wind tunnel model with piezoelectric actuators and sensors embedded in the vertical tail structure is used for the development of a mathematical plant model and experimental evaluation of various control systems.; System identification of the 4.7% scaled F-15 vertical tail model resulted in a single input single output state space model that successfully identified the 1st bending, 2nd bending and 3rd bending modes on the structure.; Noise cancellation control, optimal control and proportional integral derivative control were implemented with a digital controller to reduce vibrations in the structure. Power spectral densities show reductions of up to 80% attenuation in the structure with the application of the closed loop feedforward controller noise cancellation concept.; An analysis of wind tunnel models, piezoelectric materials, structural dynamics, system identification, digital signal processing, control system implementation and experimental validation was performed during this research and lead to an integrated study that could impact the sustainment of the aircraft.
机译：F-15飞机在高攻角下的自助激振减少了垂直尾翼的寿命，并降低了飞机的准备状态。先前的研究表明，将主动控制系统应用于F-15的双尾翼结构，可使振动降低多达50％。这项研究将噪声消除的概念应用于振动结构。比例为4.7％的F-15风洞模型具有嵌入垂直尾翼结构中的压电致动器和传感器，用于数学工厂模型的开发和各种控制系统的实验评估。通过对4.7％比例缩放的F-15垂直尾部模型进行系统识别，得出了一个单输入单输出状态空间模型，该模型成功地识别了第一个 super，第二个supersuper和三个结构上的 rd 弯曲模式。噪声消除控制，最优控制和比例积分微分控制通过数字控制器实现，以减少结构中的振动。功率频谱密度显示出，通过采用闭环前馈控制器噪声消除概念，结构中的衰减降低了80％。在此研究过程中，对风洞模型，压电材料，结构动力学，系统识别，数字信号处理，控制系统实施和实验验证进行了分析，并得出了可能影响飞机维持性的综合研究。

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