TSTO 발사체의 단분리에 관한 수치적 연구

The study of stage separation and abort simulation has always been important in the development of next-generation launch vehicles. In the present study, numerical simulation of stage separation of two-stage reusable launch vehicles was made by using a two-dimensional viscous flow solver on unstructured meshes. Aerodynamic data were obtained for a matrix of longitudinal and vertical positions in the supersonic (Mach number 3) and hypersonic (Mach number 6) speeds. For these simulation, the Langley Glide-Back Booster (LGBB) configuration in a beLLy-to-belly bimese arrangement was used. The present study was conducted to investigate the interference aerodynamic characteristics and to study the proximity flow environment. The results showed that complex bow shock interactions have an impact on the proximity aerodynamic characteristics and the stability of the vehicle during the stage separation.