Structural Dynamic Analysis of Space Launch Vehicle using Axisymmetric Shell Element including Hydroelastic Effect for Pogo Stability Analysis

Abstract

Space launch vehicle exhibits many multidiscipline-related instabilities which are caused by coupling between the fuselage structural and other subsystem components. Pogo phenomenon is one of those coupled instabilities. This thesis focuses on the pogo phenomenon which is the longitudinal dynamic instability of space launch vehicles. For the prediction of the pogo phenomenon, it is essential to establish appropriate structural modeling, the characteristics of the feedlines and propulsion system. The purpose of this thesis is conducting the modal analysis of the launch vehicles. It was conducted by using the axisymmetric two-dimensional shell elements. The present analysis was validated using examples of the existing launch vehicles. The comparison in terms of modeling and results against the