复合材料垂尾盒段力学性能研究

Research on mechanical properties of composite vertical tail box

目前复合材料垂尾已在多种型号飞机上使用,为保证设计优化和结构安全,复合材料垂尾盒段力学特性的研究十分必要。文中进行了垂尾盒段的弯扭试验,用MSC.PATRAN/NASTRAN建立了复合材料垂尾盒段的有限元模型并进行了计算。通过计算结果和试验结果的对比验证了模型的正确性。试验和模拟得出复合材料盒段力学性能。复合材料盒段加筋蒙皮受力情况十分复杂,蒙皮应变沿厚度线性分布,各层应力不是连续分布的,但是在层内却是连续分布的。加筋的存在增加了该处蒙皮的刚度,相同铺层角度的复合材料铺层沿着加筋条方向的应变分布情况相似,而且应变水平相近等。

As composite vertical tail boxes have been used for many airplanes, in order to assure the design optimization and structure security, it is very necessary to study on the mechanical properties of composite vertical tail box. A bending and torsion test on the composite vertical tail box has been carried out in this paper, the finite element model for the composite vertical tail box was established by using MSC.PATRAN/NASTRAN and the calculation has been performed. The correctness of the model was proved by comparing the calculated result with the test result. The mechanical properties of the composite box were also obtained though test and simulation. Although stress condition on the strengthened skin of composite box is very complicated, the stress of the composite laminate is distributed linearly along the thickness direction, the stress of the laminates is discontinuous among every plies but it is continuous in one ply. The girders enhance the rigidity of the strengthened skin, the stress distribution of composite plies with same ply angle is similar along the girders direction, and the stress level is very close.