МЕТОД ПРОЕКТУВАЛЬНОГО РОЗРАХУНКУ НА МІЦНІСТЬ ПОПЕРЕЧНОГО СТИКУ ПАНЕЛЕЙ ВІД'ЄМНОЇ ЧАСТИНИ КРИЛА ТА ЦЕНТРОПЛАНА ТРАНСПОРТНОГО ЛІТАКА

Abstract

Due to the limitation in the dimensions of the structural elements of the modeled wing contour and the possibility of increasing their cross-sections in the area of the transverse joint, only on the inside, there is a need to find an effective solution for the design, mass of the joint, as well as its statical strength at the modeling stage. The article presents the method and its application using the example of a preliminary analysis of the design calculation of the design of the flange connection of the center section with the outer wing section (OWS) of a transport aircraft. The method is based on the calculation of stresses caused by the discrete transmission of forces between elements. In the calculation method, a simplified statically indeterminate joint model is obtained according to the geometric characteristics and force transmission characteristics of each node section in the flange joint structure. During the calculations, the following are determined: diagrams of the bending moment and axial forces obtained using the force method, the distribution of force loads in each section of the model for subsequent analysis of the static safety factor. The resulting calculation results are compared with the airworthiness requirements to determine whether they meet the design requirements. For components with greater static strength, or those that do not meet the requirements, it is recommended to further modify the design parameters to ensure an effective design of the center section joint with the outer wing section and subsequent re-calculation. The calculation method used has practical value as a preliminary engineering analysis.The geometric characteristics of the junction of the center section with the negative part of the wing were modeled using the CAD/CAMCAE CATIA system.