A comprehensive Approach to the Assessment of a Hybrid Electric Powertrain for Commuter Aircraft

Hofmann, Jan-Philipp; Stumpf, Eike; Weintraub, Daniel J.; Koehler, Jo; Pham, Duc; Schneider, Michael; Dickhoff, Jens; Burkhart, Berhard; Reiner, G.; Spiller, Martin; Werner, Ernst August

doi:10.2514/6.2019-3678

Cited by 12 publications

(5 citation statements)

References 9 publications

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“…This approach focuses on the hybridization factor (H P ), which captures the power split between the conventional power plant and the electric motor and implements an energy-based mission analysis to determine overall fuel and battery mass. Hoffman et al [9] analyze the impact of hybridization on the DO-228 aircraft and determine that a parallel hybrid architecture with a reduced number of passengers provides improved takeoff performance and a lower noise footprint. DeVries et al [30] propose a hybrid-electric and distributed propulsion aircraft sizing methodology for regional transport aircraft.…”

Section: Literature Reviewmentioning

confidence: 99%

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Systems Integration Framework for Hybrid-Electric Commuter and Regional Aircraft

2023

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System integration is one of the key challenges to bringing future hybrid-electric and all-electric aircraft into the market. In addition, retrofitting and redesigning existing aircraft are potential paths toward achieving hybrid and all-electric flight, which are even more challenging goals from a system integration perspective. Therefore, integration tools that bridge the gap between the aircraft and the subsystem level need to be developed for use in the conceptual design stage to address current system integration challenges, such as the use of space, the share between propulsive and secondary power, required level of electrification, safety, and thermal management. This paper presents a multidisciplinary design analysis (MDA) framework that integrates aircraft and subsystem sizing tools. In addition, this paper includes improved physics-based subsystem sizing methods that are also applicable to smaller, commuter, or regional aircraft. The capabilities of the developed framework and tools are presented for a case study covering the redesign of the DO-228 with a hybrid-electric propulsion system in combination with the electrification of its systems architecture and different subsystem technologies.

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Section: Literature Reviewmentioning

confidence: 99%

“…Smaller aircraft carrying 19-30 passengers (PAX) on routes of up to 500 km may potentially benefit from hybridization [8]. The DO-228, in particular, has been used for conceptual studies and as a technology testbed on hybridization for this aircraft category [8,9].…”

Section: Introductionmentioning

confidence: 99%

Systems Integration Framework for Hybrid-Electric Commuter and Regional Aircraft

2023

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“…This aircraft has been analyzed in previous hybrid-electric aircraft studies (see, e.g., Refs. [7,46]). Moreover, performance data of the aircraft are available from multiple sources [47][48][49][50], and therefore it is well-suited as a reference configuration.…”

Section: A Definition Of Top-level Aircraft Requirements and Design A...mentioning

confidence: 99%

Cross-Validation of Hybrid-Electric Aircraft Sizing Methods

Finger

Vries

Vos

et al. 2022

Journal of Aircraft

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The number of studies on hybrid-electric aircraft is steadily increasing because these configurations can lead to lower operating costs and environmental impact than traditional aircraft. However, due to the lack of reference data of actual hybrid-electric aircraft, the design tools and results are difficult to validate. This paper analyzes the key points that must be validated when developing or implementing a hybrid-electric aircraft design tool by contrasting the assumptions and results of two independently developed sizing methods. An existing 19-seat commuter aircraft is selected as the baseline test case, and both design tools are used to size that aircraft. The aircraft is then resized 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 methods and provide a reference data set that can be used to benchmark design tools.

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“…Refs. [15,16]). Moreover, performance data of the aircraft is available from multiple sources [17][18][19][20], and therefore it is well-suited as a reference configuration.…”

Section: Fig 1 Comparison Between Do 228ng [14] (Left) and The 19-sementioning

confidence: 99%

A Comparison of Hybrid-Electric Aircraft Sizing Methods

Finger

Vries

Vos

et al. 2020

AIAA Scitech 2020 Forum

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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.

show abstract

A comprehensive Approach to the Assessment of a Hybrid Electric Powertrain for Commuter Aircraft

Cited by 12 publications

References 9 publications

Systems Integration Framework for Hybrid-Electric Commuter and Regional Aircraft

Systems Integration Framework for Hybrid-Electric Commuter and Regional Aircraft

Cross-Validation of Hybrid-Electric Aircraft Sizing Methods

A Comparison of Hybrid-Electric Aircraft Sizing Methods

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