复合材料帽型加筋层合梁刚度的理论计算研究  

Theoretical calculation of stiffness of laminated composite beam with hat-section

作　　者：胡明勇[1] 郑波[1] 王安稳[1] 

机构地区：[1]海军工程大学理学院,武汉430033

出　　处：《海军工程大学学报》2017年第6期6-12,共7页Journal of Naval University of Engineering

基　　金：国家自然科学基金资助项目(51479206);湖北省自然科学基金资助项目(2015CFC868)

摘　　要：根据层合板理论,首先利用三维应力、应变转换关系,推导出复合材料帽型加筋层合梁的总体刚度矩阵公式,建立了复合材料帽型加筋层合梁的拉伸刚度和弯曲刚度理论计算式;然后,计算了轴向或横向荷载作用下,复合材料帽型加筋悬臂层合梁的拉伸和弯曲变形,并和ANSYS有限元计算结果进行了对比;最后,计算分析了腹板倾斜角度对结构刚度的影响。计算结果表明:腹板倾斜角度为60°时,帽型加筋结构的刚度和所需材料的比值达到最优值;拉伸和弯曲刚度的理论解和ANSYS有限元计算结果吻合较好,说明上述方法以及推导的计算公式是准确、可靠的。Based on constitutive equation and deformation equation,a total stiffness matrix of laminated composite beam with hat-section is deduced by using the relation of 3D stress-stain transformation.Then the analytical calculation formulations of axial and bending stiffness of laminated composite beam with hat-section are derived.The axial and bending stiffness of laminated composite beam with T-section are calculated under the uniformly distributed load or concentrated force with various boundary condition.A comparison between analytical calculation results and ANSYS calculation results shows that they are in agreement.The results show that this method is feasible and applicable in the initial design of composite hull.

关 键 词：复合材料层合梁 帽型加筋 刚度 三维应力-应变转换关系 

分 类 号：V229.7[航空宇航科学与技术—飞行器设计]