Abstract Landing gear doors on aircraft have experienced flutter during preliminary flight testing. While designs vary widely, landing gear doors are typically plate-like structures with a relatively rigid actuator attached to their inside surface. To better understand the aeroelasticity of landing gear doors, this study investigates the aeroelastic stability of an idealized model. The model consists of a hinged plate with an interior constraint approximating the actuator attachment. The plate is subject to uniform flow, and an unsteady vortex lattice model is coupled to the structural model to predict critical flow velocities. The location and footprint area of the internal constraint, along with plate aspect and mass ratios, are varied to investigate a large parameter space. Results reveal that the critical flow speed and instability mechanism are sensitive to the postulated actuator placement. In general, flutter is the dominant mode of instability when the actuator is postulated in the leading quarter of the plate. In other postulated locations, divergence dominates. However, the exact shape and location of the boundary between flutter and divergence is configuration dependent and found to be especially sensitive to changes in aspect ratio.

中文翻译：

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亚音速势流中理想起落架门的气动弹性分析

摘要 飞机的起落架门在初步试飞过程中出现过颤动。虽然设计差异很大，但起落架门通常是板状结构，其内表面附有相对刚性的致动器。为了更好地了解起落架门的气动弹性，本研究调查了理想模型的气动弹性稳定性。该模型由一个铰接板组成，该铰接板具有近似执行器附件的内部约束。该板受均匀流动的影响，非定常涡旋晶格模型与结构模型耦合以预测临界流速。内部约束的位置和足迹面积，以及板的纵横比和质量比，会发生变化以研究大的参数空间。结果表明，临界流速和不稳定机制对假定的执行器位置很敏感。一般来说，当执行器位于板的前四分之一时，颤振是主要的不稳定模式。在其他假定的位置，分歧占主导地位。然而，颤振和发散之间边界的确切形状和位置取决于配置，并且发现对纵横比的变化特别敏感。