Structural Analysis Of Integral Fuselage Panels

Design, analysis, manufacture and experiment technology of the civil aircraft fuselage panel is one of the key technologies of trunk/jumbo aircraft in the 21st century. To provide an adequate basis for the structure design, stress analysis of the integrally fuselage panels should be carried out. An integral panel subjected to axial and shear load is analyzed respectively via three different methods-experiments, FEM, approximate computation.The engineering algorithms of these panels under the axial compression loads or shear loads are mainly studied. The calculation of the panel subjected to axial load uses the Johnson method which is quite agreed with the experiment. The calculation of the panel subjected to shear load uses a semi-empirical and semi-theoretical method of tension field analysis. Based on the structure form of the airplane, the characteristics of its loads and the way of load transfers, different finite element models are analyzed and compared. An entity model according to the true shape and the true size is created by using CATIA and then introduce it into MSC.PATRAN to create the finite element model. The result of calculation and experiment is compared。So, we can find a better method to create model which is close to the actual, and provide reference basis for the accurate calculation and structural design.