This project explores methods to build habitats on the moon. It specifically explores the design of an interior modular system for inflatable habitats. Lunar Architecture can broadly be divided into three stages, pre-integrated, semi-integrated and built on site. Pre-integrated habitats, are fully assembled on earth and shipped with a rocket to the Moon, which has initial practicality, but constrains structure size to a rockets cargo space. Inflatable habitats fall under the semi-integrated category, which means that all the added interior volume created after inflation, will need to be built out onsite. It makes most sense to design a well-functioning modular system for this purpose, as modularity can provided the required redundancy and minimize the total amount of unique parts needed. The system needs to be lightweight, compact when stored, yet versatile enough to create flexible and engaging interiors. The project asks what a self-sufficient architecture in a lunar context would look like, if it were built with a modular approach and if it is possible to create sustainable, engaging environments through modularity.

In January 2005, President Bush announced the Vision for Space Exploration. This vision involved a progressive expansion of human capabilities beyond Low Earth Orbit beginning with a return to the moon no later than 2020. Current design processes utilized to meet this vision employ performance based trade studies to determine the lowest cost, highest reliability solution. The methodology implemented in this dissertation focuses on a concurrent evaluation of the performance, cost, and reliabilities of lunar architectures. This process directly addresses the top level requirements early in the design process and allows the decision maker to evaluate the highest reliability, lowest cost lunar architectures without being distracted by the performance details of the architecture. To achieve this methodology of bringing optimal cost and reliability solutions to the decision maker, parametric performance, cost, and reliability models are created to model each vehicle element. These models were combined using multidisciplinary optimization techniques and response surface equations to create parametric vehicle models which quickly evaluate the performance, reliability, and cost of the vehicles. These parametric models, known as ROSETTA models, combined with a life cycle cost calculator provide the tools necessary to create a lunar architecture simulation. The integration of the tools into an integrated framework that can quickly and accurately evaluate the lunar architectures is presented. This lunar architecture selection tool is verified and validated against the Apollo and ESAS lunar architectures. The results of this lunar architecture selection tool are then combined into a Pareto frontier to guide the decision maker to producing the highest reliability architecture for a given life cycle cost. With this presented methodology, the decision maker can transparently choose a lunar architecture solution based upon the high level design discriminators. This method can achieve significant reductions in life cycle costs (over 40%) keeping the same architecture reliability as a traditional design process. This methodology also allows the decision maker to choose a solution which achieves a significant reduction in failure rate (over 50%) while maintaining the same life cycle costs as the point solution of a traditional design process.