Mission Analysis and Component-Level Sensitivity Study of Hybrid-Electric General Aviation Propulsion Systems

Dean, Tyler S.; Wroblewski, Gabrielle E.; Ansell, Phillip J.

doi:10.2514/6.2018-1749

Cited by 15 publications

(12 citation statements)

References 18 publications

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“…The results indicate that the two HEP concepts present no benefit with respect to a conventional powertrain. This is in line with the findings of previous studies, which show that either more optimistic e bat values [9,12,22,44] or reduced ranges [8,[17][18][19]25] are required for the HEP concepts to be competitive. However, the results obtained in this study are conservative for several reasons.…”

Section: Analysis Of Findings and Discussionsupporting

confidence: 92%

“…Despite the large amount of ongoing research related to hybrid-electric propulsion, little information is available regarding the clean-sheet design process of HEDP aircraft. In many cases, design studies analyze the hybrid-electric powertrain in detail starting from a predefined aircraft configuration [12,16,17], often maintaining the take-off weight constant [18][19][20]. Other studies have formulated more generalized conceptual sizing methods for HEP aircraft [20][21][22][23][24][25][26][27][28], but do not integrate the aero-propulsive interaction effects in the process.…”

Section: Introductionmentioning

confidence: 99%

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Preliminary Sizing Method for Hybrid-Electric Distributed-Propulsion Aircraft

Vries

Brown

Vos

2019

Journal of Aircraft

110

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Section: Analysis Of Findings and Discussionsupporting

confidence: 92%

Section: Introductionmentioning

confidence: 99%

Preliminary Sizing Method for Hybrid-Electric Distributed-Propulsion Aircraft

Vries

Brown

Vos

2019

Journal of Aircraft

110

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“…BHL conceptualized studies have pronounced a desirable SE in the range of 1000-1500 Wh/kg for HE applications in single-aisle segments [40,121]. The desired level varies based on the type of propulsion system configuration, airframe morphology, size of the aircraft, degree of hybridization, and the flown mission range [225]. The NAEreport made a consensus effort in defining the least desired SE in three different segments of aircrafts: 1.…”

Section: Pmsmmentioning

confidence: 99%

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

2020

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Electrification of the propulsion system has opened the door to a new paradigm of propulsion system configurations and novel aircraft designs, which was never envisioned before. Despite lofty promises, the concept must overcome the design and sizing challenges to make it realizable. A suitable modeling framework is desired in order to explore the design space at the conceptual level. A greater investment in enabling technologies, and infrastructural developments, is expected to facilitate its successful application in the market. In this review paper, several scholarly articles were surveyed to get an insight into the current landscape of research endeavors and the formulated derivations related to electric aircraft developments. The barriers and the needed future technological development paths are discussed. The paper also includes detailed assessments of the implications and other needs pertaining to future technology, regulation, certification, and infrastructure developments, in order to make the next generation electric aircraft operation commercially worthy.

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“…The desired technology improvement is mostly expected from the improvement in specific power/specific energy of the electrical energy storage system [19,20]. Nonetheless, efficiency of the other system components has cascading effects on the sizing of the energy storage system and therefore also plays paramount role [24]. Furthermore, limited public information was found in hybrid aircraft study from the gas turbine perspective.…”

Section: Introductionmentioning

confidence: 99%

A Framework for Optimization of Hybrid Aircraft

Zhao

Sahoo

Kyprianidis

et al. 2019

Volume 3: Coal, Biomass, Hydrogen, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organ

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To achieve the goals of substantial improvements in efficiency and emissions set by Flightpath 2050, fundamentally different concepts are required. As one of the most promising solutions, electrification of the aircraft primary propulsion is currently a prime focus of research and development. Unconventional propulsion sub-systems, mainly the electrical power system, associated thermal management system and transmission system, provide a variety of options for integration in the existing propulsion systems. Different combinations of the gas turbine and the unconventional propulsion sub-systems introduce different configurations and operation control strategies. The trade-off between the use of the two energy sources, jet fuel and electrical energy, is primarily a result of the trade-offs between efficiencies and sizing characteristics of these sub-systems. The aircraft structure and performance are the final carrier of these trade-offs. Hence, full design space exploration of various hybrid derivatives requires global investigation of the entire aircraft considering these key propulsion sub-systems and the aircraft structure and performance, as well as their interactions. This paper presents a recent contribution of the development for a physics-based simulation and optimization platform for hybrid electric aircraft conceptual design. Modeling of each subsystem and the aircraft structure are described as well as the aircraft performance modeling and integration technique. With a focus on the key propulsion sub-systems, aircraft structure and performance that interfaces with existing conceptual design frameworks, this platform aims at full design space exploration of various hybrid concepts at a low TRL level.

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Mission Analysis and Component-Level Sensitivity Study of Hybrid-Electric General Aviation Propulsion Systems

Cited by 15 publications

References 18 publications

Preliminary Sizing Method for Hybrid-Electric Distributed-Propulsion Aircraft

Preliminary Sizing Method for Hybrid-Electric Distributed-Propulsion Aircraft

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

A Framework for Optimization of Hybrid Aircraft

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