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Non-linear finite-element analyses of composite shells by total Lagrangian decomposition with application to the aircraft tire.

机译：通过总拉格朗日分解对复合材料壳体进行非线性有限元分析，并将其应用于飞机轮胎。

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A total Lagrangian finite element scheme for arbitrarily large displacements and rotations is applied to a wide range of shell geometries. The scheme decomposes the deformation into stretches and rigid-body rotations, examining the deformed state with respect to an orthogonal, rigidly translated and rotated triad located at the point of interest on the deformed structure. The Jaumann stresses and strains, which are resolved along the axes of this triad, are employed in the algorithm. Local and layer-wise thickness stretching and shear warping functions are used to model the three-dimensional behavior of the shell. These functions are developed through the use of the constitutive equations, certain stress and displacement continuity requirements at ply interfaces and laminate surfaces, and the behavior of the shell reference surface. Two finite elements are employed in the analyses: an eight-noded, 36 degree-of-freedom (DOF) element, and a four-noded, 41 DOF element. The 36 DOF element, which is not a compatible element with respect to the derivatives of in-plane deformations (i.e., {dollar}usb{lcub},x{rcub}, usb{lcub},y{rcub}, vsb{lcub},x{rcub}, {lcub}rm and{rcub} vsb{lcub},y{rcub}{dollar} are not forced to be continuous along interelement boundaries) proves adequate for moderate rotation problems, but fails in modeling very large rotation problems. The use of the 44 DOF element provides dramatically improved results in the large rotation problem. The scheme is used to analyze isotropic and anisotropic beams, plates, arches, and shells. As a special application, a detailed finite element model of an aircraft tire is analyzed with regard to deformations resulting from inflation pressure. Finally, the feasibility of static contact analysis is also demonstrated.
机译：用于任意大位移和旋转的总拉格朗日有限元方案适用于各种壳体几何形状。该方案将变形分解为拉伸和刚体旋转，相对于位于变形结构上感兴趣点的正交，刚性平移和旋转的三重轴检查变形状态。在算法中采用了沿该三重轴分解的Jaumann应力和应变。局部和逐层厚度拉伸和剪切翘曲函数用于模拟壳体的三维行为。这些功能是通过使用本构方程，层界面和层压表面的某些应力和位移连续性要求以及壳参考表面的性能来开发的。分析中使用了两个有限元：一个八节点的36自由度（DOF）元素和一个四节点的41 DOF元素。 36自由度元素，相对于平面内变形的导数不兼容（例如，{dollar} usb {lcub}，x {rcub}，usb {lcub}，y {rcub}，vsb {lcub }，x {rcub}，{lcub} rm和{rcub} vsb {lcub}，y {rcub} {dollar}没有被迫沿元素边界连续）证明适用于中等旋转问题，但是无法建模很大旋转问题。使用44自由度元件可大大改善旋转问题。该方案用于分析各向同性和各向异性的梁，板，拱和壳体。作为一种特殊应用，针对充气压力引起的变形，分析了飞机轮胎的详细有限元模型。最后，还证明了静态接触分析的可行性。

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