Integration Concept for a Hybrid-Electric Solid-Oxide Fuel Cell Power System into the X-57 “Maxwell”

Papathakis, Kurt V.; Schnarr, Otto C; Lavelle, Thomas M.; Borer, Nicholas K.; Stoia, Tina; Atreya, Shailesh

doi:10.2514/6.2018-3359

Cited by 13 publications

(8 citation statements)

References 3 publications

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“…This, combined with the battery, provides enough performance for the aircraft to maintain level flight or shallow drift-down performance, giving the operator more options for an expedited landing. These and other situations are discussed in the companion papers by Papathakis et al [5] and Woodham et al [7].…”

Section: B Hybrid-electric Sofc Power Systemmentioning

confidence: 96%

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Design and Performance of a Hybrid-Electric Fuel Cell Flight Demonstration Concept

Borer

Geuther

Litherland

et al. 2018

2018 Aviation Technology, Integration, and Operations Conference

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this technology. These drawbacks have thus far limited market penetration in all but the smallest vehicle classes. Current approaches to airborne electricity generation revolve around storage of the energy in batteries onboard the aircraft, which greatly limits range and endurance, or generation of electricity by combustion of stored hydrocarbon fuel as part of a hybrid-electric architecture, which suffers from mass and efficiency challenges.Borer [1] outlined these approaches and recommended pursuit of an additional option to the portfolio of solutions available to store energy for airborne electric propulsion. Borer proposed the use of a hybrid-electric solution that generates electricity primarily from a Solid Oxide Fuel Cell (SOFC) fed from an onboard fuel reformer, which converts heavier hydrocarbons into products suitable to be consumed by the SOFC. To be viable, this power system needs to operate at a specific power level of at least 300 W/kg and an efficiency of 60%, referenced to the lower heating value (LHV) of the stored fuel. These characteristics represent significant advances in the state-of-the-art for hybrid-electric SOFC architectures -a recent National Academies report indicated that such architectures are capable of a specific power of 100 W/kg and an efficiency of 30-40% [2]. More recent research suggests that higher specific power and efficiency levels are achievable [3].This paper is one of a number of concurrent papers related to NASA's Fostering Ultra-Efficient, Low-Emitting Aviation Power (FUELEAP) project. The authors present a detailed application of a hybrid-electric, heavy-fuel, SOFC power system developed under FUELEAP. Specifically, this paper describes the integration of a 120 kW power system in place of the battery system used on NASA's X-57 "Maxwell" distributed electric propulsion (DEP) technology flight demonstrator. Section II provides background on FUELEAP and the X-57 program. Section III describes the integration of the hybrid-electric SOFC power architecture onto the X-57 and provides performance estimates for two different design spirals, as well as comparison to gasoline-fueled and battery-powered alternatives. Finally, Section IV summarizes the results of this research. Other companion papers include: a more detailed description of the power system design [4], electrical integration of this power system into the X-57 [5], thermal cycle testing of SOFC hardware to assess suitability for aviation operations [6], system safety analysis of the FUELEAP X-57 demonstrator concept [7], and the use of model-based systems engineering frameworks to aid in the development of future demonstrator concepts [8].

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Section: B Hybrid-electric Sofc Power Systemmentioning

confidence: 96%

“…The traction bus voltage of the hybrid-electric SOFC power system must be designed to be compatible with the X-57's existing electrical system, resulting in a range of 416-525 VDC. More details on the electrical system integration can be found in a companion paper by Papathakis et al [5].…”

Section: A Requirementsmentioning

confidence: 99%

Design and Performance of a Hybrid-Electric Fuel Cell Flight Demonstration Concept

Borer

Geuther

Litherland

et al. 2018

2018 Aviation Technology, Integration, and Operations Conference

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“…There is a plenty of research investment exploring this technology. NASA led Fostering Ultra Efficient Low Emitting Aviation Power (FUELEAP) program focuses on development of stack technology for a 120 kW SOFC system and processing of hydrocarbon fuel [222,223]. Bauhaus Luftfahrt led AdVanced Aircraft CONcepts (AVACON) project researches on H 2 fueled PEM cell for APU application [224].…”

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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“…Papathakis et al's 20 study is related to the national aeronautics and space administration works, NASA is actively developing new electric and hybrid‐electric aircraft propulsion technologies as part of the aeronautics strategic implementation plan. The NASA X‐57 ‘Maxwell’ aircraft is the first all‐electric, manned using distributed electric propulsion technology, and is expected to establish greater efficiency and reduced emissions as compared to the more conventional airframe and propulsion configuration.…”

Section: Introductionmentioning

confidence: 99%

Development and evaluation of an integrated solid oxide fuel cell system for medium airplanes

Evrin

Dinçer

2020

Int J Energy Res

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This paper concerns a solid oxide fuel cell (SOFC) based integrated powering system for a medium-sized airplane and analyzes it thermodynamically for its performance assessment and evaluation. It further investigates the system in relation to aircraft operating conditions and provides the conceptual solutions for heating and cooling at various temperatures. The results of the energy and exergy analyses and performance assessments of the proposed integrated system are presented and discussed. The exergy and energy efficiencies of the main components are calculated and observed for the SOFCs with the maximum values of 84.54% and 80.31%, respectively. The present integrated system has overall energy and exergy efficiencies of 57.53% and 47.18%, respectively. Furthermore, it is found that an increase in the reforming temperature ratio can improve the hydrogen yield. However, when the system is operated at a temperature higher than 800 C, the hydrogen yield decreases since a reverse water gas shift reaction is more pronounced. Moreover, the SOFC shows the best performance at 800 C with a maximum power density of 1.23 W/cm 2 .

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Integration Concept for a Hybrid-Electric Solid-Oxide Fuel Cell Power System into the X-57 “Maxwell”

Cited by 13 publications

References 3 publications

Design and Performance of a Hybrid-Electric Fuel Cell Flight Demonstration Concept

Design and Performance of a Hybrid-Electric Fuel Cell Flight Demonstration Concept

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

Development and evaluation of an integrated solid oxide fuel cell system for medium airplanes

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