ROCKET-POWERED SINGLE-STAGE VEHICLE CONFIGURATION SELECTION AND DESIGN

A reusable rochet-powered, single-stage launch vehicle has been design ed as a part of the Advanced Manned Launch System study to examine opt ions for a next-generation manned space transportation system. The con figuration selection process used a response surface methodology for m ultidisciplinary optimization. The methodology was used to determine t he minimum dry weight entry vehicle to meet constraints on landing vel ocity and on subsonic, supersonic, and hypersonic trim and stability. Once the optimum configuration was determined, a multidisciplinary con ceptual vehicle design was performed. This paper presents the results of the configuration selection methodology and summarizes the overall conceptual design process with special attention given to the individu al disciplines of weights/sizing, structures/materials, configuration, flight mechanics, aerodynamics, aeroheating, propulsion, and operatio ns.