Weights and sizing assessment in the context of small launcher design

The paper presents mathematical models that can be used to quickly define preliminary key aspects regarding the sizing and weight characteristics of studied small launchers. The tool developed based on the proposed mathematical models can be used for standalone liquid propelled stage design or it can be integrated in an iterative multidisciplinary optimisation design scheme (MDO) for a preliminary small launcher design, able to insert the desired payload into a predefined orbit.