Transient Time Aeroelastic Analysis for a Supersonic Flight vehicle with a Ramjet Engine

Abstract

This paper presents a transient time aeroelastic analysis for a supersonic flight vehicle with a ramjet engine. First, computational fluid dynamics (CFD) is conducted to estimate its baseline geometry and the prediction results obtained upon the vehicle surface are transferred to the structural transient time analysis. The structural analysis is then carried out. A brand new finite element domain decomposition structure analysis is developed for the present transient time aeroelastic analysis. To solve a resulting large-scale system equation, FETI method is adopted for the present shell analysis. And comparison results between the present transient time FETI and Dual-primal FETI methods are attempted. During the 500 time steps, both analyses show good agreement with a difference less than 0.01% for the example problem. As a result, a detailed analytical procedure for the transient time aeroelastic analysis is established to predict a possibility of an excessive deformation or buckling induced in the supersonic vehicle during flight.