Systems Integration Processes for NASA's Crew Launch Vehicle
- Paper number
IAC-06-D2.7.-A3.7.01
- Author
Mr. James Taylor, National Aeronautics and Space Administration (NASA)/Marshall Space Flight Center, United States
- Coauthor
Mr. James Reuter, National Aeronautics and Space Administration (NASA)/Marshall Space Flight Center, United States
- Coauthor
Mr. Jeff Sexton, National Aeronautics and Space Administration (NASA)/Marshall Space Flight Center, United States
- Coauthor
Mr. Michael L. Burris, National Aeronautics and Space Administration (NASA)/Langley Research Center, United States
- Year
2006
- Abstract
NASA’s Exploration Initiative will require development of many new elements to constitute a robust system of systems. New launch vehicles are needed to place cargo and crew in stable low earth orbit. This paper examines the systems integration processes NASA is utilizing to ensure integration and control of propulsion and non-propulsion elements within NASA’s Crew Launch Vehicle (CLV). The objective of the CLV is to provide the transportation capabilities to meet the Constellation Program requirements for delivering a Crew Exploration Vehicle (CEV) or other payload to Low Earth Orbit (LEO) in support of the lunar and Mars missions. The CLV must successfully provide the capability within cost and schedule with an acceptable risk approach. This paper will describe in detail the systems engineering management processes that will be applied to assure CLV Project success through complete and efficient technical integration. Discussion of specific processes for requirements development and verification, integrated design and analysis, integrated simulation and testing and the integration of reliability, maintainability and supportability (RMS) into the design will also be included. The CLV Project is broken logically into elements by the major hardware groupings, and associated management, system engineering, and integration functions. The processes to be described herein are designed to integrate within these CLV elements and among the other Constellation projects. Launch vehicle stack integration (CLV to CEV, and Ground and Flight Operations integration) throughout the life cycle, including integrated vehicle performance through orbital insertion, recovery of the first stage, and reentry of the upper stage will also be discussed. The processes for decomposing requirements to the Elements and ensuring that requirements have been correctly validated, decomposed, allocated, and that the verification requirements are properly defined to ensure that the system design meets requirements will be discussed.
- Abstract document
- Manuscript document
IAC-06-D2.7.-A3.7.01.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.