Methodology and tools for propulsive performance characterization of high-speed aircraft in conceptual design

The worldwide growing attention to reduce the environmental impact of civil aviation in the next future is clearly visible. At the same time, the goal of achieving high flight speeds is becoming ever more important. During the first parts of the design process, when a quick response to each design modification is required, it is important to have simple and reliable tools to estimate the performances of such vehicles. The aim of the thesis is the development of methodologies and tools for the characterization of propulsive performance of high-speed aircraft in conceptual design. The results of this work allow the evaluation of basic performances for different hypersonic air-breathing propulsive systems architecture and the upgrade of the mathematical models implemented in ASTRID-H tool, a conceptual design tool currently under development by Politecnico di Torino. The first part of the research activity carried out for this project have been focusing on the analysis of currently existing engines models for propulsion performance characterization and adequate for conceptual design. Then, thermodynamic models used for subsonic and supersonic engines are implemented and validated with vehicles data, found in literature. Hypersonic engine models are finally designed. Study is made on STRATOFLY MR3 vehicle concept allows 300 passengers to move between places located at the antipodes in few hours, reaching Mach 8 cruise speed, using Liquid Hydrogen as propellant, avoiding the emission of CO2. This aircraft is based on LAPCAT MR2.4 project and it integrates two combined thermodynamic cycle: Air Turbo Rocket (ATR) is a rocket-based air-breathing engine which are responsible to propel the aircraft from take-off till high-supersonic cruise of Mach 4; after that, vehicle thrust is provided by Dual-Mode Ramjet (DMR), an air-breathing engine that can work in a ramjet configuration (subsonic combustion) or in scramjet one (supersonic combustion). Different models of the two engines are built and analysed, starting from the classic thermodynamic cycle. Finally, Graphical User Interface is implemented, allowing interactive use of propulsive models by a possible user, who does not necessarily have to know the detailed implementation of programmes.