A Comparison of Hybrid-Electric Aircraft Sizing Methods

Abstract

The number of case studies focusing on hybrid-electric aircraft is steadily increasing, since these configurations are thought to lead to lower operating costs and environmental impact than traditional aircraft. However, due to the lack of reference data of actual hybrid-electric aircraft, in most cases, the design tools and results are difficult to validate. In this paper, two independently developed approaches for hybrid-electric conceptual aircraft design are compared. An existing 19-seat commuter aircraft is selected as the conventional baseline, and both design tools are used to size that aircraft. The aircraft is then re-sized under consideration of hybrid-electric propulsion technology. This is performed for parallel, serial, and fully-electric powertrain architectures. Finally, sensitivity studies are conducted to assess the validity of the basic assumptions and approaches regarding the design of hybrid-electric aircraft. Both methods are found to predict the maximum takeoff mass (MTOM) of the reference aircraft with less than 4% error. The MTOM and payload-range energy efficiency of various (hybrid-) electric configurations are predicted with a maximum difference of approximately 2% and 5%, respectively. The results of this study confirm a correct formulation and implementation of the two design methods, and the data obtained can be used by researchers to benchmark and validate their design tools.

Aero-Propulsive Efficiency Requirements for Turboelectric Transport Aircraft

“…This method has been validated by comparing the results to an independently-developed HEP sizing routine in Ref. [41]. The baseline requirements, design parameters, and assumptions can be found in Ref.…”

Synthesis of Aero-Propulsive Interaction Studies Applied to Conceptual Hybrid-Electric Aircraft Design

“…The sizing methodology that is followed is illustrated graphically in Figure 2; the full description of the Class-I DHEP sizing method can be found in Ref. [27] The hybrid electric preliminary sizing method developed by de Vries et al [27] has been compared to another sizing approach as developed by Finger et al [35]; the comparison of both methods in Finger et al [36] shows good agreement between results.…”

A Review of Concepts, Benefits, and Challenges for Future Electrical Propulsion-Based Aircraft

“…This is proposed for finding the optimal power schedule for a hybrid electric distributed propulsion (HEDP) system configuration but based on the low-fidelity aerodynamics tool. Finger et al [147] presented a comparison of the sizing methodology on a 19 PAX aircraft to check for the potential and validity in both sizing methodologies.…”