Performance analysis of a hybrid-electric retrofit of a RUAG Dornier Do 228NG

Juretzko, Philipp Georg; Immer, Marc; Wildi, Jörg

doi:10.1007/s13272-019-00420-2

Cited by 12 publications

(11 citation statements)

References 17 publications

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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%

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

confidence: 99%

“…Some studies retrofit an existing aircraft with hybridelectric propulsion (HEP) to analyze a specific aspect of the technology, maintaining takeoff mass constant (e.g., Refs. [7][8][9]). Others actively resize the aircraft to allow a fair comparison with a conventional reference aircraft (e.g., Refs.…”

mentioning

confidence: 99%

Cross-Validation of Hybrid-Electric Aircraft Sizing Methods

Finger

Vries

Vos

et al. 2022

Journal of Aircraft

View full text Add to dashboard Cite

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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.

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“…Battery mass mainly depends on two factors. First, it is highly dependent on the operating strategy, as stated by Juretzkok et al [16]. Secondly, it depends on absolute power demand.…”

Section: Introductionmentioning

confidence: 99%

Conceptual design and comparison of hybrid electric propulsion systems for small aircraft

Kohler

Jeschke

2021

CEAS Aeronaut J

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This paper presents a novel conceptual design method for electric and hybrid electric propulsion systems in small aircraft. The effects of key design parameters on the propulsion system performance are analyzed and the advantages and drawbacks of the investigated propulsion systems are discussed on the basis of two sets of thrust requirements. First, the general conceptual design algorithm is outlined. This is followed by a description of the three propulsion systems investigated: the fully electric; the parallel hybrid; and the conventional internal combustion engine. Scalable models of all required propulsion system components are presented, including weight estimation and operating characteristics. Afterwards, the conceptual design algorithm is exemplified for a reference two-seater motorized glider with a cruising speed of 140 kt and a maximum take-off mass of 1000 kg. Key design parameters are identified and their impact on propulsion system mass and cruise efficiency discussed. This study suggests that the parallel hybrid propulsion system is advantageous for high power ratios between take-off and cruise. For a power ratio of 4.5, either a relative cruise efficiency advantage of 12% or a maximum system mass advantage of 10% can be expected, depending on the propeller design. For the chosen cruise range of 300 km, the system mass of the fully electric propulsion system is at least 2.37 times higher when compared to the conventional propulsion system. In summary, a design method for hybrid electric propulsion systems is presented here which may be used for conceptual design. Furthermore, the suitability of the propulsion systems under investigation for different sets of thrust requirements is assessed, which may be helpful for aircraft designers.

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Performance analysis of a hybrid-electric retrofit of a RUAG Dornier Do 228NG

Cited by 12 publications

References 17 publications

Cross-Validation of Hybrid-Electric Aircraft Sizing Methods

Cross-Validation of Hybrid-Electric Aircraft Sizing Methods

A Comparison of Hybrid-Electric Aircraft Sizing Methods

Conceptual design and comparison of hybrid electric propulsion systems for small aircraft

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