Structures and materials technology issues for reusable launch vehiclesProjected space missions for both civil and defense needs require significant improvements in structures and materials technology for reusable launch vehicles: reductions in structural weight compared to the Space Shuttle Orbiter of up to 25 percent or more, a possible factor of 5 or more increase in mission life, increases in maximum use temperature of the external surface, reusable containment of cryogenic hydrogen and oxygen, significant reductions in operational costs, and possibly less lead time between technology readiness and initial operational capability. In addition, there is increasing interest in hypersonic airbreathing propulsion for launch and transmospheric vehicles, and such systems require regeneratively cooled structure. The technology issues are addressed, giving brief assessments of the state-of-the-art and proposed activities to meet the technology requirements in a timely manner.
Document ID
19860047794
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dixon, S. C. (NASA Langley Research Center Hampton, VA, United States)
Tenney, D. R. (NASA Langley Research Center Hampton, VA, United States)
Rummler, D. R. (NASA Langley Research Center Hampton, VA, United States)
Wieting, A. R. (NASA Langley Research Center Hampton, VA, United States)
Bader, R. M. (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB OH, United States)