Functional Architecture Design of a Lunar Habitable Module through Model-Based Systems Engineering

The growing complexity of engineering systems in the last few years has proved the need for a systematic approach to their management and design. This need is most clearly seen in the aerospace industry, where the interdependence between subsystems requires methodologies and tools capable of coping with complex interdependencies throughout the whole project lifecycle. In this context, Model-Based Systems Engineering (MBSE) is adopted through the Arcadia methodology, which organizes the system into four levels: operational, system, logical, and physical. Each level guides and aligns with the next, thus maintaining the traceability and consistency of the requirements provided by stakeholders, from the design phase up to the complete physical implementation of the system. This thesis proposes the creation of a functional and logical architecture model of a lunar multi-purpose habitat, starting from the system level and proceeding to the logical breakdown of all subsystems that constitute the overall system architecture. For the development of the model, the MBSE tool Capella was used, which supports the multi-level representation of complex systems according to the Arcadia approach. The work focused mainly on identifying the main functions of the system, represented in the System Analysis level, and then continued with the Logical Architecture, where these functions were broken down and allocated to the subsystems. A top-down strategy was adopted, based on a gradual functional decomposition. Functional exchanges, logical interfaces, functional chains, operational modes, and scenarios were modeled using the tools provided by the Capella environment. Functional requirements were imported into the model through ReqIF (Requirements Interchange Format) files generated by DOORS, a requirements management tool, allowing vertical traceability throughout the modeling process. The final model represents an architectural baseline, serving as a reference for the next phases of the system’s physical design. The final diagrams provide a starting point for the system avionics, supporting the transition to the definition of physical components and their real interfaces. This work confirms the effectiveness of the MBSE approach and the Capella tool in designing complex space systems, while also revealing some critical issues related to advanced scripting functions and the reliance on external tools, such as M2Doc, for exporting content. These elements suggest possible future improvements in the overall modeling process.