Zhyriakov D. Method of integrated design and construction of joints of main ribs with monolithic panels of the wing of an aircraft of the transport category

The dissertation is devoted to solving the scientific and technical problem of developing a method of integrated design and construction of joints of main ribs with monolithic panels of the wing of an aircraft of the transport category to improve the efficiency of domestic aircraft of the transport category. The choice of purpose is determined by the need for new scientific developments and the development of new methods of design, construction, production and testing. In this work, a method of integrated design of the joints of main rib and the monolithic wing’s panel using a parametric model of the wing’s section with modern computer-aided design systems CAD/CAM/CAE was developed. In the work, the author touched upon the issue of prototyping an aircraft design. At the design stages, prototyping helps to obtain the optimal design, check it for working capacity, think over the manufacture with minimal cost and with the required quality. For the first time, the method of prototyping in the design of an aircraft structure using a 3D printer and FDM technology was proposed. New methods of integrated design of the joints of the main rib and the monolithic wing panel using computer-aided design systems CAD/CAM/CAE have been developed and implemented. Parametric modeling was performed using the Siemens NX computer-integrated system. New methods of definitions the aerodynamic characteristics of the wing were mastered and implemented, taking into account using wing high-lift devises and determination of both the general and local stress-strain state of the wing structural elements with the help of numerous methods (finite element methods), which made it possible to obtain both an automated change in the calculation parameters and to obtain more accurate results. Analyses of the study of the local stress-strain state in the area of joint of the main rib and the monolithic wing panel was showed. The optimal radius of rounding in the zone of local thickening in terms of minimum mass and minimum stress was determined. The nature of the distribution of the locally stress-strain state in the area of the fastener hole was shown for plate that biaxial loading. In addition, the action of a load that simulates a shear load in a joint was considered (load between shear tie and skin).