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An Economic and Technical Analysis of a Partially Reusable Space Vehicle System
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1967 by SAE International in United States
Annotation ability available
Event: Space Technology Conference
The operating costs of current space systems are examined briefly to determine the distribution of these costs through the major operational elements of the systems. For flight frequencies of between 5-20 flights per year, the system costs associated with recovery and reuse are examined to show where major savings are potentially achievable. The authors then describe the results of a feasibility analysis of a vehicle concept emphasizing recovery and reuse of the spacecraft and the simplification of the expendable elements. The latter is accomplished by incorporating the boost phase steering function in the spacecraft and using solid propellant motor booster stages.
A first order cost comparison with other current and projected concepts is then presented to indicate the separate effect on operating costs of launch vehicle propulsion type, spacecraft type, and steering techniques. The authors conclude with an enumeration of study results which indicate that the partially reusable head-end steering concept is technically feasible and cost effective.
CitationHislop, S., Fuller, G., and Ugoretz, K., "An Economic and Technical Analysis of a Partially Reusable Space Vehicle System," SAE Technical Paper 670397, 1967, https://doi.org/10.4271/670397.
- Fuller G. M., “A Feasibility Study of Head-End Steering for a Simplified Manned Space Vehicle,” Douglas Aircraft Co., Huntington Beach, California, Report No. SM 48152, December 1964. (U)
- Fuller G. M., “Phase II Study of Head-End Steering for a Simplified Manned Space Vehicle,” Douglas Aircraft Co., Huntington Beach, California, Report No. SM 51872, March 1966. (U)
- Whiting T. R., “Design Considerations of Reusable Launch Vehicles - Final Report,” Douglas Aircraft Co., Santa Monica, California, Report No. DAC-57913, October 1966. (C)
- “Study of a Ballistics Re-entry - Type Logistics Spacecraft,” Lockheed California Company, Report LR17477, February 12, 1966. (U)
- Dawson R. P., “Saturn IB Improvement Study - (Solid First Stage) Phase II,” Douglas Aircraft Company, Huntington Beach, California, Report SM-51816, January 11, 1966. (U)
- “Mission Requirements of Lifting Systems-Engineering Aspects,” McDonnell Aircraft Corporation, St. Louis, Missouri, Report No. B831, August 1965. (C)
- “Modified Apollo Logistics Spacecraft Study - Final Report,” North American Aviation, Inc., Los Angeles, California, Report SID 63-1461-7, December 30, 1963. (C)
- “Mission Requirements of Lifting Systems - Operational Aspects,” The Boeing Company, Seattle, Washington, Report D2-82531, August 1965. (U)