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针对航空用纤维复合材料,基于纤维与基体的协调变形规律和材料应变能密度的计算,导出了纤维复合材料的刚度表达式,研究了刚度矩阵的基本力学特性,给出了复合材料刚度矩阵元素与基体材料的刚度、纤维束的刚度及铺设方向的关系,提供了平面铺层和三维取向纤维复合材料的基本刚度设计公式和设计方法。最后给出工程应用设计方法的几个具体例子,并与其他理论和实验结果进行了对比。研究结果表明,在考虑材料制备工艺缺陷造成的刚度折减后,本文提出的设计公式及方法可应用于纤维复合材料的优化设计。
Based on the coordinate deformation law of fiber and matrix and the calculation of material strain energy density, the stiffness expression of fiber composites is derived. The basic mechanical properties of stiffness matrix are studied. The stiffness matrix elements And the stiffness of the matrix material, the stiffness of the fiber bundle and the laying direction, provides the basic stiffness design formula and design method of the flat laminate and the 3D oriented fiber composite material. Finally, several concrete examples of engineering application design methods are given and compared with other theoretical and experimental results. The results show that the design formulas and methods proposed in this paper can be applied to the optimal design of fiber composites after considering the stiffness reduction caused by the defects of material preparation process.