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A study of active trim panels for interior noise reduction in an aircraft fuselage

机译：用于飞机机身的内部降噪主动调整面板的研究

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An experiment has been conducted to evaluate the use of force actuators on an aircraft fuselage model interior trim panel as the control element for active control of interior noise. These experiments were conducted on a composite model of a commuter class aircraft. A trim panel was designed specifically for this evaluation, constructed in three large sections and hard mounted to the ring frames of the primary structure. Piezoceramic actuators were bonded to the outer surface of the trim panels. Studies of the interior pressure response due to both the primary source alone and control source(s) alone were conducted as well as the control cases. Initial results provided global reductions of 5 dB for the case where the response was dominated by an acoustic resonance. In all other cases, only local reductions at the error microphones were attained. This was attributed to very strong mismatches between the interior response driven by the primary source and that driven by the control sources. This result is in strong contrast to previous results attained for control actuators attached to the primary structure.
机译：已经进行了一个实验，以评估使用力执行器在飞机机身模型内饰面板中的使用作为控制元件，用于有源控制内部噪声。这些实验是在通勤级飞机的复合模型上进行的。专为该评估设计了一个修剪面板，在三个大部分中构造并硬安装到主要结构的环形框架中。压电织式致动器粘合到装饰板的外表面上。仅进行单独的主要源和控制源引起的内部压力响应以及对照情况。初始结果为响应以声响谐振占主导地位的情况提供了5 dB的全球减少。在所有其他情况下，达到了误差麦克风的局部减少。这归因于由主要来源驱动的内部响应和由控制源驱动的内部响应之间的非常强烈的不匹配。该结果与先前的结果具有强烈的对比，该结果达到了附着在主要结构上的控制执行器。

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