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首页> 外文会议>International Conference on Adaptive Structures and Technologies; 20051009-12; Paris(FR) >CONCEPTUAL SKIN DESIGNS FOR MORPHING AIRCRAFT
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CONCEPTUAL SKIN DESIGNS FOR MORPHING AIRCRAFT

机译：用于飞机变形的概念皮肤设计

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摘要

A two step optimization process is described to develop the distribution of materials and geometry for flexible skins. The skins are able to handle out-of-plane loads associated with aerodynamic loading while simultaneously allowing a wing substructure to under go large structural deformations. This requires the skin to simultaneously have low in-plane stiffness and high bending stiffness. The first step involves determining the bulk material properties required from the skin and the geometry describing the attachment to the substructure. For this step, a 3-layer physical model is described that takes in to account the structural mechanism, skin, and mechanism-skin connections in addition to aerodynamic loads. The optimization problem is developed using the Solid Isotropic Material Penalization method. Results from this step are the distribution of bulk material properties across a model wing structure. The next step assumes that the skin is a heterogeneous material. An optimization process is described based on a multi-objective function which minimizes the sum of the strain energy and mutual potential energy. An example is presented for a skin element subjected to deformation under shear loading as the wing is sweep in shear.
机译：描述了两步优化过程，以开发柔性蒙皮的材料和几何形状分布。蒙皮能够处理与空气动力负荷相关的平面外负荷，同时允许机翼下部结构承受较大的结构变形。这要求皮肤同时具有低的面内刚度和高的弯曲刚度。第一步涉及从表皮和描述与基础结构的连接的几何形状确定所需的散装材料特性。对于此步骤，将描述一个三层物理模型，该模型考虑了除空气动力学载荷之外的结构机制，蒙皮以及机制-蒙皮连接。使用固态各向同性材料罚分法开发了优化问题。该步骤的结果是散装材料特性在模型机翼结构上的分布。下一步假定皮肤是异质材料。基于多目标函数描述了一个优化过程，该函数将应变能和互势能之和最小化。提出了一个示例，该示例针对蒙皮元素在机翼进行剪切扫掠时在剪切载荷下变形的情况。

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