Accurate dry mass prediction is essential in early design phases of a launch system. To predict structural mass
of a launch vehicle more accurate at a conceptual design phase, a structural mass model was developed. The model
predicts a launch vehicle’s structural mass, thickness, center of mass and mass moment of inertia. Load carrying
structures within in a conventional launch vehicle were modeled on a subsystem level by determining force and
moment acting on the structure during flight. The model was developed for use in launch vehicle optimization
algorithms, and thus relies on a relative small amount of calculations to obtain structural strength of parts. The
model supports walls made of isotropic and orthotropic material, sandwich panels, rings and stiffeners. The model
was compared to existing models and known data from existing launch vehicles. The results did indicate a good
convergence for determining wall thickness when compared to values found in literature.