A Model-Based Systems Engineering approach to the conceptual design of an adaptable Small Solar System Body Lander

Abstract

Standardization is becoming more commonplace in space missions, aiming to increase reliability and drive down costs. Due to the relative similarities in operating environment between Small Solar System Bodies (SSSBs), a highly-adaptable lander may be able to service a majority of SSSBs with minor adaptations. The model-based systems engineering (MBSE) framework is implemented to enable agile development. The key enabling subsystems required for landing are defined, resulting in an impact dampening and a rebound suppression subsystem. Concepts for these subsystems are evaluated and traded-off. A number of astrodynamics simulations for the trajectory dynamics is made using Tudat for each SSSB, to find maximum deployment height and impact speed. The detailed subsystem design focuses on finding a suitable, highly-adaptable, commercial-off-the-shelf solution; with different variants of the final design allocated to each SSSB. Lastly, the scalability of the key enabling subsystems is analyzed. This results in the complete conceptual design of a highly-adaptable SSSB lander.