Abstract

This document presents the development and application of unsteady aerodynamic, structural dynamic, and aeroelastic reduced-order models (ROMs) for the ascent aeroelastic analysis of the Ares I-X ight test and Ares I crew launch vehicles using the unstructured-grid, aeroelastic FUN3D computational uid dynamics (CFD) code. The purpose of this work is to perform computationally-e cient aeroelastic response calculations that would be prohibitively expensive via computation of multiple full-order aeroelastic FUN3D solutions. These e cient aeroelastic ROM solutions provide valuable insight regarding the aeroelastic sensitivity of the vehicles to various parameters over a range of dynamic pressures.

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