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Zero Poisson's Ratio Cellular Honeycombs for Flex Skins Undergoing One-Dimensional Morphing

机译:零泊松比蜂窝状蜂窝状皮肤一维变形。

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Cellular honeycomb cores with overlying flexible face sheets have been proposed for use as flex skins for morphing aircraft. The cellular cores, which provide underlying support to the face sheets for carrying aerodynamic loads, must have low in-plane stiffness and high in-plane strain capability. For one-dimensional morphing applications such as span-, chord-, or camber-change, restraining the Poisson's contraction (or bulging) that a conventional cellular honeycomb core would otherwise experience in the non-morphing direction results in a substantial increase in the effective modulus in the morphing direction. To overcome this problem, this article develops zero Poisson's ratio hybrid and accordion cellular honeycombs. Cellular Material Theory is extended, and analytical solutions for the mechanical properties and global strains of the hybrid and accordion cellular honeycombs are developed. The analytical results show excellent agreement with ANSYS finite element results. Comparing the properties shows that the hybrid and accordion honeycombs proposed have generally similar in-plane axial stiffness and strain capabilities to conventional honeycombs when the latter are unrestrained in the non-morphing direction. However, with the zero Poisson's ratio of the hybrid and accordion honeycombs, it is observed that the axial stiffness in the morphing direction will not increase when the skins are restrained in the non-morphing direction. The zero Poisson's ratio of the accordion and hybrid cellular honeycombs is not helpful from an out-of-plane load carrying ability standpoint. However, the out-of-plane load carrying ability of the accordion honeycombs can be superior to those of conventional honeycombs if the 'continuous fibers' are sufficiently thick, leading to a very large modulus in the non-morphing direction. The effective out-of-plane stiffness of hybrid cellular honeycombs, on the other hand, is poorer than conventional cellular honeycombs.
机译:已经提出具有上覆的柔性面板的蜂窝状蜂窝芯用作飞机变形的柔性表皮。为面板提供底层支撑以承受空气动力载荷的蜂窝状芯必须具有较低的平面内刚度和较高的平面内应变能力。对于一维变形应用,例如跨度,和弦或外倾变化,限制常规蜂窝状蜂窝芯会在非变形方向上经历的泊松收缩(或凸出)会导致有效变形的显着提高变形方向的模量。为了克服这个问题,本文开发了零泊松比混合和手风琴蜂窝状蜂窝。扩展了蜂窝材料理论,并开发了混合和手风琴蜂窝蜂窝的力学性能和整体应变的分析解决方案。分析结果表明与ANSYS有限元结果具有极好的一致性。比较性能表明,当常规蜂窝在非变形方向上不受约束时,提出的混合蜂窝和手风琴蜂窝具有与常规蜂窝大致相似的面内轴向刚度和应变能力。然而,观察到杂化和手风琴蜂窝的泊松比为零时,观察到当皮肤在非变形方向上受到约束时,变形方向上的轴向刚度不会增加。从平面承载能力的角度来看,手风琴和混合蜂窝蜂窝的零泊松比没有帮助。但是,如果“连续纤维”足够粗,则手风琴蜂窝的平面外承载能力会优于常规蜂窝,从而导致在非变形方向上的模量非常大。另一方面,混合蜂窝状蜂窝的有效面外刚度比常规蜂窝状蜂窝差。

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