Maximum Take-Off Mass Estimation of a 19-Seat Fuel Cell Aircraft Consuming Liquid Hydrogen

Abstract

In this paper, the maximum take-off mass (MTOM) of a 19-seat fuel cell aircraft with similar characteristics to a conventional 19-seat aircraft is estimated using the combination of a rapid method and semi-empirical equations. The study shows that the MTOM of a 19-seat fuel cell aircraft with current technology would be 25% greater than that of a conventional aircraft. However, with the expected technological improvements, the MTOM of a 19-seat fuel cell aircraft could reach lower values than that of a conventional aircraft. The most important parameter affecting the MTOM of fuel cell aircraft is the power-to-weight ratio of the fuel cells. If this ratio of fuel cell aircraft does not improve significantly in the future, fuel cell aircraft with lower power loading will become the preferred choice; thus, certain trade-offs in flight performance, such as a longer takeoff distance, will be accepted. The study provides the basis for further economic analysis of fuel cell aircraft, which has yet to be conducted.