Development of Superconducting Propulsion System with Liquid Hydrogen Cooling for Future Electric Aircraft

2022 ◽

pp. 62-73

Author(s):

Dmitry Dezhin ◽

Roman Ilyasov

Keyword(s):

Electric Propulsion ◽

Fem Simulation ◽

Synchronous Generator ◽

Liquid Hydrogen ◽

Propulsion System ◽

Moscow Aviation Institute ◽

Cross Sectional ◽

Electric Propulsion System ◽

The Future ◽

Hydrogen Cooling

The use of liquid hydrogen as a fuel will be inevitable in the aviation of the future. This statement means that manufacturers will also implement liquid hydrogen for cooling all superconducting aviation equipment of an electric propulsion system. The development of fully electric aircraft is the most promising solution in this case. Scientists from the Department of electrical machines and power electronics of Moscow aviation institute have conducted calculations and theoretical researches of critical specific mass-dimensional parameters (MW/ton and MW/m3 at 21 K) of fully superconducting aviation synchronous generator of the electric propulsion system. The results are in this article. The article discusses the results 3D finite element modeling (FEM) simulation of a 5 MW fully superconducting synchronous generator with combined excitation. Superconducting armature and axial excitation windings based on second generation high temperature superconductors (HTS-2G) are located on the stator, which makes it possible to contactlessness and the absence of sliding seals. A dry gap will reduce gas-dynamic losses and increase the nominal peripheral speed of the rotor. The use of liquid hydrogen as a coolant makes it possible to significantly increase the linear load of the generator, and high current densities to reduce the cross-sectional area of the coils, which will make it possible to place them in individual cryostats in the future. Individual cryostats will allow to remove the heat release of magnetic losses from the cryogenic zone and reduce the consumption of refrigerant. For the purpose of internal redundancy of the HTS coils, the machine has a complete set of reserve winding made of ultrapure aluminum, also cooled by liquid hydrogen. If the superconducting coils get out of the stand, the generator will provide 15 % power on standby

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Research on Parameters Matching of Ultralight Electric Aircraft Propulsion System

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.732-733.1212 ◽

2013 ◽

Vol 732-733 ◽

pp. 1212-1215

Author(s):

Gui Wen Kang ◽

Yu Hu ◽

Ya Dong Li ◽

Wen Hui Jiang

Keyword(s):

Electric Propulsion ◽

High Energy ◽

Low Noise ◽

Electric Power System ◽

Propulsion System ◽

Heat Radiation ◽

Design Parameters ◽

Electric Propulsion System ◽

Electric Aircraft ◽

Parameter Matching

The propulsion system of ultralight electric aircraft is one of the general aviation technology development directions. It has the advantages such as light pollution, low noise, high energy utilization ratio, simple structure, easy maintenance, high reliability, less heat radiation, little operation cost and so on. Combined with the certain type of ultralight aircraft design parameters, the layout of aircraft electric propulsion, the principles and steps of the parameter matching of electric propulsion system were presented. The method of parameter matching and performance verification of electric propulsion system was put forward. The feasibility of the system is verified from the point of dynamic property. The study of parameter matching of electric propulsion system could not only provide basis for the integrated optimization for electric power system, but also evaluate the performance of the system simulation as reference.

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

Aerospace ◽

10.3390/aerospace7040044 ◽

2020 ◽

Vol 7 (4) ◽

pp. 44 ◽

Cited By ~ 5

Author(s):

Smruti Sahoo ◽

Xin Zhao ◽

Konstantinos Kyprianidis

Keyword(s):

Technological Development ◽

Propulsion System ◽

New Paradigm ◽

Modeling Framework ◽

Future Technology ◽

Electric Aircraft ◽

Electrical Propulsion ◽

Development Paths ◽

System Configurations ◽

Insight Into

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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Design, Fabrication and Analysis of an Electric Ducted Fan

Volume 1: Compressors, Fans, and Pumps; Turbines; Heat Transfer; Structures and Dynamics ◽

10.1115/gtindia2019-2620 ◽

2019 ◽

Author(s):

Parthasarathy Vasanthakumar ◽

Jigme Tsering ◽

Sumanth Siddhartha Suddunuri

Keyword(s):

Rapid Development ◽

Propulsion System ◽

Basic Principles ◽

Blade Element Theory ◽

Ducted Fan ◽

Ansys Cfx ◽

Electric Aircraft ◽

Feasible Option ◽

Efficient Combustion ◽

Battery Technology

Abstract Driven by rapid development in battery technology and increase in scope for electric air taxi vehicles, developing an efficient combustion free propulsion system to pair with an electric aircraft is crucial for future of aircraft industry. However, with current technology, ducted fan configuration engines are the only feasible option when it comes to combustion free propulsion system which are already being used in many unmanned drones and unmanned aerial vehicles. In the present work, simple design, analysis and fabrication of ducted fan is performed. Propeller fan and duct is designed using basic principles of blade element theory and momentum theory. Using the parameters from the theoretical design phase, 3D model is made and fabricated using 3D printing and assembled to fit with tolerances suitable for mounting motor. A test stand capable of measuring thrust by varying rpm is designed and built using Arduino based interface. Finally, the designed model is analyzed in Ansys CFX for thrust output using an MRF simulation.

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