Reusable Booster System Review and Assessment (2012) / Chapter Skim
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Appendix E: Selected Reusable Launch Vehicle Development History
Appendix E: Selected Reusable Launch Vehicle Development History
Pages 95-99
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From page 95... ...
In 1971, the Office of Management and Budget direction constrained the space shuttle overall development cost and limited the annual funding for development to approximately half that estimated to be required for the fully reusable two-stage configuration. These budgetary constraints forced NASA to consider other alternatives, which ultimately resulted in the partially reusable configuration known today.
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From page 96... ...
cross-range requirements drove the configuration and added complexity; · Continuous additional requirements were introduced during the development process; and · The complexity of the configuration and its resulting sensitivity and required interactivity provided design challenges, which affected the operational complexities and flight constraints. Even if the original, totally reusable two-stage human-rated space shuttle system had been properly funded from the outset, it is doubtful that the initial low cost goals would have been met.
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From page 97... ...
Moreover, government and contractor laboratories had fabricated and tested large titanium aluminide panels under approximate vehicle operating conditions, and NASP contractors had fabricated and tested titanium aluminide composite pieces. When NASP was cancelled, the government admitted to making a $1.7 billion investment in the National Aerospace Plane, but parts of the research and development were classified, and the official costs may have been higher.2 Lessons learned from the NASP program include the following: · SSTO vehicle technologies using airbreathing engines are beyond the existing state of the art; · Aerothermodynamics of sustained flight at high hypersonic speed within the atmosphere creates significant challenges with regard to materials and thermal management; and · Propulsion technology should be independently matured prior to initiation of large-scale vehicle development programs.
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From page 98... ...
Making a stage larger helps, but adding thermal protection for reentry, aerodynamic surfaces for lift and control, landing gear, and life support for manned use makes meeting the 0.88 minimum mass fraction requirement extremely difficult. X-33 was to address and demonstrate the many technology issues associated with meeting this requirement.
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From page 99... ...
With these considerations, there are clear differences between the RBS concept and previous RLV programs. And, while efficient reusability remains an elusive goal for launch, the committee believes that the RBS concept represents a logical compromise between fully reusable and fully expendable systems that is technically achievable in a well-structured program.
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