Projected 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% 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.
Structures and Materials Technology Issues for Reusable Launch Vehicles
1985
30 pages
Report
Keine Angabe
Englisch
Unmanned Spacecraft , Airframes , Composite materials , Dynamic loads , Hypersonic vehicles , Reusable launch vehicles , Weight reduction , Systems analysis , Aerothermodynamics , Air breathing boosters , Cost reduction , Cryogenic fluid storage , Heat transfer , Refractory materials , Satellite lifetime , Thermal protection
Engineering Index Backfile | 1964
|Elsevier | 1985
|Reusable Launch Vehicles Outlook - Launch Vehicles Table
Online Contents | 2009