Structural Design Analysis of a Reusable Launch Vehicle's Wings

Abstract

This thesis is focused on the structural analysis of aerodynamic surfaces, particularly wings, from first stages or boosters from fully and partially reusable launch vehicles. Specific cases include the Space Liner booster, but it is also applicable to other winged surfaces from launch vehicles and aircraft. The SpaceLiner project aims to combine the space launch sector with the commercial aviation sector. This spaceplane consists of 2 stages: a crewed passenger stage and a uncrewed booster stage that doubles as a reusable launch vehicle for heavy payloads. The focus of this thesis is the booster stage wings. This project investigates different types of mass estimation methods as well as similar concept designs, in order to aid the mass estimation and design process of the booster stage wings. In addition to research, the loading and wing parameters are considered in order to analyze, optimize, and model a design for the booster stage wings. By determining the structural composition and necessary thickness of the wing frame, an overall mass estimation is performed.