Crew Launch Vehicle First Stage Design, Development, Test and Evaluation
- Paper number
IAC-06-D2.7.-A3.7.02
- Author
Mr. Michael L. Burris, National Aeronautics and Space Administration (NASA)/Langley Research Center, United States
- Coauthor
Mr. Richard Burt, National Aeronautics and Space Administration (NASA)/Marshall Space Flight Center, United States
- Year
2006
- Abstract
The Crew Launch Vehicle (CLV) is an integral part of NASA’s Exploration architecture that will provide crew and cargo access to the International Space Station as well as low earth orbit support for lunar missions. Currently in the system definition phase, the CLV is planned to replace the Space Shuttle for crew transport in the post 2010 time frame. It is comprised of a solid rocket booster first stage derived from the current Space Shuttle SRB, a LOX/hydrogen liquid fueled second stage utilizing a derivative of the Space Shuttle Main Engine (SSME) for propulsion, and a Crew Exploration Vehicle (CEV) composed of Command and Service Modules. This paper deals with current DDT\&E planning for the CLV first stage solid rocket booster. Described are the current overall point-of-departure design and booster subsystems, systems engineering approach, and milestone schedule requirements.
- Abstract document
- Manuscript document
IAC-06-D2.7.-A3.7.02.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.