Automated approach to weight estimating for reusable launch vehicle concepts

Automated systems are described which estimate vehicle and launch system mass properties with perturbation of mission requirements and/or vehicle design characteristics and geometries. Weight is a major criterion in the selection between single-stage-to-orbit and two launch systems. Efforts have been directed toward developing mass property predicting computer programs to accommodate both systems. Automated programs which allow rapid and consistent concept evaluation are discussed and indicated schematically. Incorporated into vehicle and launch system weight is vehicle shape and structural concept. To this end, automated sizing programs allow variation in payload weight and volume, propellant tankage concepts, and environmental protection systems in combination with wing and empennage geometry modifications. Trade data developed from these systems are presented together with sample program weights for the SS.