Static Aeroelastic Analysis on Two Stage Rocket Body

Abstract

In the design of a rocket, aeroelastic effects are rarely taken into account. But in real life, aeroelasticity plays an important role in deciding the performance of a rocket. This paper involves the aeroelastic analysis over a two stage rocket body with the simulation of fluid-structural interactions, initially starts with flow analysis over the geometry at different Mach numbers 1.5, 2.5 and 3 followed by structural analysis by linking the pressure distribution over the body obtained. Software's going to be used in this thesis is CATIA for modeling the object and then continued in ANSYS Workbench for Meshing and FLUENT for Flow analysis followed by Static Structural Analysis in workbench. After obtaining pressure distribution over the body, Normal force is going to be calculated using Numerical calculations. Thus the behaviour of Static Aeroelastic response over two stage rocket body is going to be predicted.