A Lunar Exploration Architecture Design and Decision Environment
- Paper number
IAC-05-D2.3.05
- Author
Dr. Douglas Stanley, Georgia Institute of Technology, United States
- Coauthor
Mr. Dean Bucher, Georgia Institute of Technology, United States
- Coauthor
Mr. David Reeves, Georgia Institute of Technology, United States
- Coauthor
Dr. Alan Wilhite, United States
- Year
2005
- Abstract
A Lunar Exploration Architecture Design and Decision Environment Alan W. Wilhite, Douglas O. Stanley, Dean Bucher, and David Reeves Georgia Institute of Technology/National Institute of Aerospace Modern system engineering architecture design tools and processes, including multi-attribute decision approaches, were used to revisit the Apollo Lunar Orbit Rendezvous decision over the initially favored Lunar Direct or Earth Orbit Rendezvous. In addition, other architectures, development approaches, and technologies were analyzed to ascertain the advancements that could be achieved over the original Apollo architecture to meet the requirements of NASA’s current human Lunar/Mars exploration program. A modern, systems engineering approach (the Georgia Tech Integrated Product/Process Development) used to flow down requirements and to conduct an initial architecture assessment. These results were structured in a Quality Functional Deployment process and matrix to visualize the relationship between stakeholder requirements, engineering requirements, technical performance measures, threshold values, initial competitor architecture assessment, and engineering and organizational risks. A prioritized list of engineering requirements was developed to determine the range of architectures and technologies to be assessed and to define the basic requirements for the decision analysis and the supporting architecture simulation environment. A multidisciplinary architecture simulation environment (ASE) was developed based on the information required for the architecture selection decision. The environment includes the capability to assess weight, performance, cost, risk, and reliability/safety. The ASE uses a weighted multi-attribute decision matrix to select preferred architecture approaches. The environment was initially validated by anchoring all weight, performance, and cost results with actual historical data and requirements from Apollo. The three major Apollo architecture options were modeled and the historic decision selecting Lunar Orbit Rendezvous was revisited using a multi-attribute decision approach. Alternate architectures were then developed using requirements from NASA’s current human Lunar/Mars exploration program. Weights, performance, and cost data were updated to reflect modern technology and development approaches. The ASE was used to perform a variety of trade studies and derive a preferred architecture approach. The final decision analysis showed the effect of each critical attribute, combination of attributes, and the effects of uncertainty and risk.
- Abstract document
- Manuscript document
IAC-05-D2.3.05.pdf (🔒 authorized access only).
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