Roadmap for the Technological Development of Hybrid Electric and Full-Electric Propulsion Systems of Aircrafts

Varyukhin, Anton; Zakharchenko, V. S.; Vlasov, A V; Gordin, Mikhail V.; Ovdienko, Maxim

doi:10.1109/icoecs46375.2019.8949910

Cited by 10 publications

(4 citation statements)

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“…Fuel consumption is a crucial parameter that must be estimated for aircraft propulsion. For a PEM fuel cell that uses pure Hydrogen to generate electricity, the Hydrogen mass flow rate can be calculated as follows 25 _ m H 2 ¼ 1:08 × 10 À8 W s (37) The power in equation ( 36) is in watt, and the Hydrogen mass flow rate in equation ( 37) is in kg/s.…”

Section: Pem Fuel Cellmentioning

confidence: 99%

“…37 Although the DEAThruster in this study is designed toward a compact thruster with less than 10 kg/s air mass flow rate, it is superior to the rivals configured based on the conventional technologies, and based on upcoming technologies, it can be a practical alternative to replace commercial gas turbine propulsions regarding thrust density, size, and weight for coming decades. 37…”

Section: Comparison and Evaluationmentioning

confidence: 99%

“…The energy source considered for the thruster is a PEM fuel cell encompassing 33 cells that need to generate up to 150 kW power in different flight conditions to supply the thruster, which is in the scale of the commercially available PEMFC. 37 Although the DEAThruster in this study is designed toward a compact thruster with less than 10 kg/s air mass flow rate, it is superior to the rivals configured based on the conventional technologies, and based on upcoming technologies, it can be a practical alternative to replace commercial gas turbine propulsions regarding thrust density, size, and weight for coming decades. 37…”

Section: Comparison and Evaluationmentioning

confidence: 99%

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A novel full-electric aircraft propulsion based on the DEA compressor

Aryana¹

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article introduces a novel full-electric aircraft propulsion designed based on the DEA compressor, named DEAThruster that is supplied by a PEMFC. The thruster designed and modeled in this study is a compact DEAThruster to operate in altitudes up to 15,000 m and in the subsonic/transonic region with a specific thrust around 8300 N s/kg. The results show the thruster can satisfy all expectations, and it can generate up to 8300 N s/kg specific thrust for flight conditions encompassing static condition at sea level up to flight Mach number 0.95 in altitude 15,000 m. The DEAThruster can potentially be a practical alternative for gas turbine propulsions in all aspects when all available options for full-electric propulsions are not competitive for conventional aircraft propulsions in performance, size, and weight.

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Section: Pem Fuel Cellmentioning

confidence: 99%

Section: Comparison and Evaluationmentioning

confidence: 99%

Section: Comparison and Evaluationmentioning

confidence: 99%

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A novel full-electric aircraft propulsion based on the DEA compressor

Aryana¹

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…That is why electric propulsion is gaining popularity in all transport applications. However, this technological breakthrough requires an ambitious roadmap, particularly in the aeronautics sector [2]. These requirements aim to improve the performance of existing electrical equipment and find solutions to increase power density, efficiency, facilitate manufacturing or reduce volume and cost [3].…”

Section: Introductionmentioning

confidence: 99%

Comparison between Space Mapping and Direct FEA Optimizations for the Design of Halbach Array PM Motor

et al. 2022

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Effective methods for the design of high-performance electrical machines must use optimization techniques and precise and fast physical models. Convergence, precision and speed of execution are important issues, in addition to the ability to explore the entire domain of solutions. The finite element method (FEM) presents a high accuracy in the results but with high computational costs. Analytical models, on the other hand, solve the problem quickly but compromise the accuracy of the results. This work shows a comparison between an optimization made with an analytical electromagnetic model and a direct optimization with finite element field calculation for the optimal design of a Halbach array permanent magnet synchronous motor (PMSM). In the case of the analytical model, it is necessary to use an iterative method of correcting the model to obtain a valid solution. This method is known as Space Mapping (SM) and the analytical model can be improved with a reduced number of iterations with the FEM. The results show a rapid convergence towards an optimal solution for the SM, with more than 78% reduction in computational cost compared to a Direct FEM optimization. Both solutions have only a difference of 3% on the power density, which indicates that FEM does not improve the results obtained by SM. This represents a great advantage that allows for the consideration of a large amount of designs to analyze the domain of solutions in more detail. This study also shows that SM is a powerful method to optimize the power density or torque density of electrical machines.

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