Degtiarov M. Selection of rational parameters and reduction of material consumption of tail compartments of launch vehicles

The dissertation is devoted to the development of an approach to the systematic design of the tail compartments of launch vehicles based on the analysis of non- uniformity of stress distribution, physical experimental research and virtual experiment with the use of modern finite element computer technologies. An algorithm for computer modeling of the behavior of the shell structure of the tail compartment of the launch vehicles of variable stiffness using the finite element method and a new approach to the weight optimization of thin-walled wafer shell structures have been developed and applied. Using a semi-empirical method of finding the heat flux, a numerical analysis of the nonstationary stress-strain state of the holding compartment caused by temperature fields caused by the flow of the supersonic flow of combustion products of the marching propulsion system was performed. The technique is developed and the experimental research of a stress-strain condition of a tail compartment of variable rigidity at static loading is carried out. With the help of the developed approach, the tail section of the Antares launch vehicle was optimized for the first time. A numerical- experimental approach to system design and calculation of the unsteady stress-strain state of the tail section has been introduced into design practice at Design Bureau “Yuzhnoe” named after M.K. Yangel”.