航空复合材料加筋板压缩屈曲及后屈曲力学性能

航空复合材料加筋板由于具有良好的力学性能,广泛地应用于航空结构中。本工作研究了航空复合材料加筋板压缩屈曲及后屈曲力学性能,首先应用工程方法对复合材料加筋板进行压缩稳定性计算,得到加筋板的屈曲载荷和破坏载荷的预估值;其次,开展复合材料加筋板压缩稳定性实验,得到实验件的屈曲及破坏形式、实验件的载荷-应变及载荷-位移关系和实验件的屈曲载荷和破坏载荷。结果表明:采用工程方法得到的计算结果与实验结果较为吻合,屈曲载荷和破坏载荷的误差分别为6.12%和9.31%,合理应用工程方法可以为实验提供较好的指导;加筋板的破坏形式为壁板的分层、鼓包和撕裂、筋条的断裂以及筋条-壁板的脱粘;屈曲比为1.65的复合材料加筋板具有较强的后屈曲承载能力;工程中可充分应用加筋板的后屈曲承载能力提高结构的利用效率。

Compressive bucking and post-bucking mechanical properties of aeronautic composite stiffened panel

Aeronautical composite stiffened panels are widely used in aeronautical structure design because of their good mechanical properties. In this paper,the compressive buckling and post-buckling mechanical properties of aeronautical composite stiffened panels were studied. Firstly,the compressive stability of composite stiffened panels was calculated by engineering method,and the predictions of the buckling and failure loads of stiffened panels were obtained;Secondly, the compression stability experiment of the composite stiffened plate is carried out,and the buckling and failure modes,the load-strain and load displacement relationship of the experimental piece,and the buckling and failure loads of the experimental piece are obtained. The results show that the calculated results by engineering method are in good agreement with the test results,and the error of buckling load and failure load are 6.12% and 9.31% respectively. The reasonable application of engineering method can provide better guidance for the experiment;The failure modes of stiffened panels are the delamination of the panels,the bulging and tearing of the skin,the fracture of the stiffeners and the debonding of the stiffeners-panels. The buckling ratio of composite stiffened plates is 1.65,the composite stiffened plates have strong post-buckling bearing capacity;The post-buckling bearing capacity of stiffened plates can be fully applied in engineering to improve the utilization efficiency of structures.