High-energy metal fuels for rocket propulsion: characterization and performance

摘要: paper describes a joint international effort to improve solid propellant performance within the framework of FP7 European Project. Several metallized rocket propellants, broad family AP/HTPB/Metal in ratio 68/14/18, were experimentally analyzed seeking optimize delivered specific impulse by identifying most suitable high-energy fuel. Keeping same nominal composition, different metallic fuels (including micrometric and nanometric Al, AlH3, variety dual metal compositions) characterized, tested, contrasted conventional aluminum (30 µm average grain size) certified for space flights. In order overcome intrinsic limitations matrix AP/HTPB, new consisting ADN/GAP satisfying also need environmentally benign formulation was considered as well. A comparative analysis between two systems terms ideal thermochemistry experimental combustion properties reveals advantages disadvantages both. Overall, it is judged worthwhile develop with or without fuels, enhance current status propulsion. Controlling morphology mechanical compositions understanding their flame structure aggregation/agglomeration are main issues still challenging industrial users.