为改善汽车吸能盒在低速碰撞情况下的力学表现,将一种新型具有负泊松比效应的多胞结构设计为汽车前纵梁的吸能盒.通过对新型负泊松比多胞结构形状参数的研究,确立了多胞结构中特定的元胞几何参数及元胞层数作为优化变量,结构质量以及所...为改善汽车吸能盒在低速碰撞情况下的力学表现,将一种新型具有负泊松比效应的多胞结构设计为汽车前纵梁的吸能盒.通过对新型负泊松比多胞结构形状参数的研究,确立了多胞结构中特定的元胞几何参数及元胞层数作为优化变量,结构质量以及所吸收的能量作为优化目标.首先通过最优拉丁超立方的方法在变量空间内进行样本点的选取并采用ABAQUS进行有限元仿真计算,然后由Isight软件根据样本点的计算结果对优化变量与优化目标建立三阶响应面模型,最终采用NCGA对响应面模型进行优化.将优化结果进行RCAR(Research Council for Automobile Repairs)标准模型仿真计算,结果验证了这一新型负泊松比吸能盒可以在较小的质量下满足RCAR低速碰撞标准.展开更多
This paper is categorized into two parts. （1） A frame work to design the aircraft wing structure and （2） analysis ofa morphing airfoil with auxetic structure. The developed design frame work in the first part is u...This paper is categorized into two parts. （1） A frame work to design the aircraft wing structure and （2） analysis ofa morphing airfoil with auxetic structure. The developed design frame work in the first part is used to arrive at the sizes of the various components of an aircraft wing structure. The strength based design is adopted, where the design loads are extracted from the aerodynamic loads. The aerodynamic loads acting on a wing structure are converted to equivalent distributed loads, which are further converted point loads to arrive at the shear forces, bending and twisting moments along the wing span. Based on the estimated shear forces, bending and twisting moments, the strength based design is employed to estimate the sizes of various sections of a composite wing structure. A three dimensional numerical model of the composite wing structure has been developed and analyzed for the extreme load conditions. Glass fiber reinforced plastic material is used in the numerical analysis. The estimated natural frequencies are observed to be in the acceptable limits. Furthermore, the discussed design principles in the first part are extended to the design of a morphing airfoil with auxetic structure. The advantages of the morphing airfoil with auxetic structure are （i） larger displacement with limited straining of the components and （ii） unique deformation characteristics, which produce a theoretical in-plane Poisson＇s ratio of -1. Aluminum Alloy AL6061-T651 is considered in the design of all the structural elements. The compliance characteristics of the airfoil are investigated through a numerical model. The numerical results are observed to be in close agreement with the experimental results in the literature.展开更多
文摘为改善汽车吸能盒在低速碰撞情况下的力学表现,将一种新型具有负泊松比效应的多胞结构设计为汽车前纵梁的吸能盒.通过对新型负泊松比多胞结构形状参数的研究,确立了多胞结构中特定的元胞几何参数及元胞层数作为优化变量,结构质量以及所吸收的能量作为优化目标.首先通过最优拉丁超立方的方法在变量空间内进行样本点的选取并采用ABAQUS进行有限元仿真计算,然后由Isight软件根据样本点的计算结果对优化变量与优化目标建立三阶响应面模型,最终采用NCGA对响应面模型进行优化.将优化结果进行RCAR(Research Council for Automobile Repairs)标准模型仿真计算,结果验证了这一新型负泊松比吸能盒可以在较小的质量下满足RCAR低速碰撞标准.
文摘This paper is categorized into two parts. （1） A frame work to design the aircraft wing structure and （2） analysis ofa morphing airfoil with auxetic structure. The developed design frame work in the first part is used to arrive at the sizes of the various components of an aircraft wing structure. The strength based design is adopted, where the design loads are extracted from the aerodynamic loads. The aerodynamic loads acting on a wing structure are converted to equivalent distributed loads, which are further converted point loads to arrive at the shear forces, bending and twisting moments along the wing span. Based on the estimated shear forces, bending and twisting moments, the strength based design is employed to estimate the sizes of various sections of a composite wing structure. A three dimensional numerical model of the composite wing structure has been developed and analyzed for the extreme load conditions. Glass fiber reinforced plastic material is used in the numerical analysis. The estimated natural frequencies are observed to be in the acceptable limits. Furthermore, the discussed design principles in the first part are extended to the design of a morphing airfoil with auxetic structure. The advantages of the morphing airfoil with auxetic structure are （i） larger displacement with limited straining of the components and （ii） unique deformation characteristics, which produce a theoretical in-plane Poisson＇s ratio of -1. Aluminum Alloy AL6061-T651 is considered in the design of all the structural elements. The compliance characteristics of the airfoil are investigated through a numerical model. The numerical results are observed to be in close agreement with the experimental results in the literature.
