Hybrid Propulsion For A Moon Sample Return Mission

A hybrid propulsion mission to the Moon with the goal of sample return is designed and analysed based on the knowledge gained with hybrid propulsion at the University of Stuttgart and the DLR Lampoldshausen. Advantages and disadvantages are compared and the feasibility of an European Technology Demonstrator Mission is checked. A trajectory analysis of a launcher is done in order to estimate the possible payload in Moon transfer orbit. This payload is the reference mass for the analysed spacecrafts. Six different variants of hybrid propulsion spacecraft are designed and compared, as well as two liquid propulsion spacecraft. The performance is compared and the payload in form of sample return mass is determined. Hybrid propulsion with new advanced fuels that take advantage of liquefying melt layers can provide higher thrust to weight ratios than classical fuels and therefore enable missions with hybrid propulsion that until recently seemed unfeasible. The payload of a high performance hybrid propulsion spacecraft is comparable to liquid propellant systems and at the same time uses green propellants and offers a low-cost approach by reducing development and operation costs.