The objective of this study was to make estimates of the weight savings that might be realized on all the subsystems on an advanced rocket-powered shuttle (designated Shuttle 2) by using advanced technologies having a projected maturity date of 1992. The current Shuttle with external tank was used as a baseline from which to make the estimates of weight savings on each subsystem. The subsystems with the greatest potential for weight reduction are the body shell and the thermal protection system. For the body shell, a reduction of 5.2 percent in the weight of the vehicle at main engine cutoff is projected through the application of new technologies, and an additional configuration-based reduction of 5 percent is projected through simplification of body shape. A reduction of 5 percent is projected for the thermal protection system through experience with the current Space Shuttle and the potential for reducing thermal protection system thicknesses in selected areas. Main propellant tanks are expected to increase slightly in weight. The main propulsion system is also projected to increase in weight because of the requirement to operate engines at derated power levels in order to accommodate one-engine-out capability. The projections for weight reductions through improvements in the remaining subsystems are relatively small. By summing all the technology factors, a projected reduction of 16 percent in the vehicle weight at main engine cutoff is obtained. By summarizing the configurational factors, a potential reduction of 12 percent in vehicle weight is obtained.
Shuttle to Shuttle 2: Subsystem Weight Reduction Potential (Estimated 1992 Technology Readiness Date)
1988
54 pages
Report
No indication
English
Manned Spacecraft , Space shuttles , Spacecraft configurations , Spacecraft design , Weight reduction , Spacecraft construction materials , Avionics , Delta wings , Fuselages , Honeycomb structures , Landing gear , Orbit maneuvering engine (Space shuttle) , Propulsion system configurations , Sandwich structures , Tail assemblies , Thermal protection
Estimated shuttle loading emissions
NTRS | 1978
|Space Shuttle antenna subsystem design
NTRS | 1974
|Space Shuttle Orbital Maneuver Subsystem
AIAA | 1975
|Space Shuttle aft Propulsion Subsystem
AIAA | 1981
|