Evaluation of Potential Propulsion Systems for a Commercial Micro Moon Lander

Abstract: In the advent of Space 4.0 era with the commercialization and increased accessibility of space, a requirement analysis, trade-off options, development status and critical areas of a propulsion system for a Commercial Micro Moon Lander is carried out. An investigation of a suitable system for the current mission is examined in the frame of the ASTRI project of OHB System AG and Blue Horizon. Main trajectory strategies are being investigated and simulations are performed to extract the ∆V requirements. Top-level requirements are extracted which give the first input for the propulsion design. An evaluation of the propulsion requirements is implemented which outlines the factors that are more important and drive the propulsion design. The evaluation implements a dual comparison of the requirements where weighting factors are extracted, resulting the main drivers of the propulsion system design. A trade-off analysis is performed for various types of propulsion systems and a preliminary selection of a propulsion system suitable for the mission is described. A first-iteration architecture of the propulsion, ADCS and GNC subsystems are also presented as well as a component list. A first approach of the landing phase is described and an estimation of the required thrust is calculated. A unified Bipropellant propulsion system is proposed which fills out most of the mission requirements. However, the analysis shows that the total mass of the lander, including all the margins, exceeds a bit the mass limitations but no the volume limitations. The results shows that a decrease in payload capacity or the implementation of a different trajectory strategy can lower the mass below the limit. In addition, further iterations in the lander concept which will give a more detailed design, resulting to no extra margins, can drive the mass below the limit. Finally, a discussion on the results is done, addressing the limitations and the important factors that need to be considered for the mission. The viability of the mission due to its commercial aspect is being questioned and further investigation is suggested to be carried out on the ”micro” lander concept.