Conceptual design and operating costs estimation of a subsonic airliner powered by liquid hydrogen

This thesis focuses on researching the feasibility and competitiveness of a subsonic passenger transport aircraft powered by liquid hydrogen as energy source. To begin, the analysis delves into the technology of utilizing liquid hydrogen as a fuel, assessing the current state of the art and future research prospects. The investigation primarily centers on two critical aspects: the economic and technological aspects. In the process of designing such an aircraft, it's essential to comprehend the technical specifications of hydrogen tanks and how they impact the aircraft's interior layout and overall mass. However, to adequately evaluate the competitiveness of this solution, it is equally crucial to analyze the associated cost of this fuel. The conceptual design process of the aircraft follows the methodology developed by Raymer. This includes calculating the maximum takeoff mass, creating a payload-range graph, and constructing the matching chart. Additionally, a preliminary sketch of the aircraft is provided. Subsequently, the analysis extends to determining the operational costs of the aircraft, following the Roskam method. This entails estimating the direct and indirect costs associated with the aircraft's operation, as well as evaluating the economic impact this new technology would have on the entire life cycle of the aircraft. Finally, the thesis concludes with a comparison between the costs of a traditional aircraft and those of the innovative aircraft. This comparison aims to estimate the cost difference that passengers would need to sustain to fly on an aircraft capable of significantly reducing pollutant emissions.