This thesis develops a parametric framework for the sizing of the primary structure of a pressurized rover, with the objective of identifying minimum-mass configurations while satisfying the main structural constraints. The model considers geometric parameters and structural element properties as design variables and evaluates performance under representative critical conditions, such as lunar surface operations and launch environment loads. Verification criteria include allowable stress limits and dynamic requirements associated with launch-induced vibrations. The framework is implemented in a Matlab environment and interfaced with commercial FEM software (MSC Patran/Nastran) to enable automated structural analyses. The developed architecture autonomously generates numerical models consistent with user-defined inputs and returns result matrices suitable for parametric analyses and sensitivity studies.