The rapidly expanding space sector is at the forefront of innovation. New technologies are been continuously developed to allow more availability of space for a multitude of commercial or scientific goals. The same is especially true for the field of Space propulsion, where the focus is towards more compact and greener solutions, for launchers, satellites and landers. One of the most suitable candidates for chemical propulsion is the use of liquid oxygen in combination with liquid hydrogen, which, however, comes with many drawbacks connected primarily to the low energetic density of liquid hydrogen and the complexity of storing cryogenics. An innovative solution to this challenge comes with the use of Metal oxidation or metal combustion reaction. This implies the use of the reaction between air and metals or between water and metals to generate heat, power and hydrogen. This allows for much easier power generation since metal powders are simple to stock and have a much higher density than hydrogen. Therefore, the process is compact and completely renewable. The technology has undoubted potential for space applications too. The high energy density, the lack of cryogenics, the high availability and the re-usability make this technology suitable for power generation purposes and, in this case, for propulsive purposes. This thesis aims to explore the various applications of metal combustion, with a particular focus on space propulsion applications. The gathered literature will be then used to produce a conceptual design of a novel propulsion system which maximises the benefits of metal combustion.

<p dir="ltr">Current mission plans for harvesting lunar resources require further investigation of technological and energy requirements to do so. This paper presents an analysis of the thermodynamics involved in hydrogen (H₂) evolution and liquefaction within this scope. It highlights the use of solar-powered systems for electrolysis and membrane separation as efficient means to produce H₂ on the lunar surface. The study compares energy requirements and logistical considerations of in-situ resource utilization (ISRU) against transporting precursors from Earth, where the energy penalty stands at 540 MJ/kg. It is argued that an ISRU solution stands to present the most energy efficient option, particularly with the use of an active magnetic regenerative refrigeration (AMRR) system for liquefaction. Furthermore, an AMRR system also makes the currently proposed plan of shipping methane (CH₄) from the Earth for H₂ production more favorable than implementing ISRU with the state-of-the-art (SOA) reverse turbo-Brayton cryocoolers (RTBC). This emphasizes the significance of an AMRR system for H₂ production and the need for further research in its development. Additionally, this study underscores the significance of regenerative technologies and advanced life support systems for sustainable off-planet human habitation, particularly in the context of lunar and Martian missions.</p>

In this work, the use of a lunar regolith simulant as feedstock for the direct ink writing additive manufacturing process is explored, the purpose of which is to enable future lunar in-situ resource utilisation. The feasibility of this approach is demonstrated in a laboratory setting by manufacturing objects with different geometries using methyl cellulose or sodium alginate as binding agents and water as liquid phase together with the lunar regolith simulant EAC-1A to create a viscous, printable ‘ink’ that is used in combination with a custom three-axis gantry system to produce green bodies for subsequent sintering. The sintered objects are characterised using compressive strength measurements and scanning electron microscopy (SEM). It is proposed that the bioorganic compounds used in this work as additives could be produced at the site for a future lunar base through photosynthesis, utilising carbon dioxide exhaled by astronauts together with the available sunlight, meaning that all the components used for the dispersion – additive, water (in the form of ice) and regolith – are available in-situ. The compressive strength for sintered samples produced with this method was measured to be 2.4 MPa with a standard deviation of 0.2 MPa (n = 4). It is believed, based on the high sample porosity observed during SEM analysis, that the comparatively low mechanical strength of the manufactured samples is due to a non-optimal sintering procedure carried out at a too-low temperature, and that the mechanical strength could be increased by optimising the sintering process further.