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WEVJ
Special Issues
Electric and Hybrid Electric Aircraft Propulsion Systems
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Electric and Hybrid Electric Aircraft Propulsion Systems

A special issue of World Electric Vehicle Journal (ISSN 2032-6653).

Deadline for manuscript submissions: 30 November 2024 | Viewed by 2668

Special Issue Editors

Prof. Dr. Kaushik Rajashekara

E-Mail Website
Guest Editor
Department of Electrical and Computer Engineering, University of Houston, Houston, TX 77204, USA
Interests: power electronics and drive systems; subsea electrical systems; transportation electrification: electric, hybrid, and fuel cell vehicle; electric and hybrid electric aircraft, vtol, and flying cars; renewable energy and microgrids
Special Issues, Collections and Topics in MDPI journals
Dr. Hao Huang

E-Mail Website
Guest Editor
Department of Electrical and Computer Engineering, University of Houston, Houston, TX 77204, USA
Interests: aircraft main engine starter/generators (S/G) having regenerative and sensorless commutation capabilities; dual spool electrical power extractions from aircraft engines; silicon carbide (SiC) based AI

Special Issue Information

Dear Colleagues,

Electrified aircraft propulsion is a key enabling technology for achieving net zero emissions in air transportation. As in automotive systems, various electric and hybrid electric architectures, including hydrogen-based systems, have been proposed for aircraft propulsion.  In addition, significant advancements have been made in regular and flying cars and eVTOL vehicles as air taxis. This has been possible with the advances in electric machines, power electronics, energy storage systems, systems integration, control, and thermal management. The airborne vehicles' electrical components and systems must meet stringent power density, efficiency, reliability, and safety requirements. This Special Issue on “Electric and Hybrid Electric Aircraft Propulsion Systems” invites original research papers that address the challenges and opportunities in the following topics:

  • Electric, hybrid, and distributed propulsion system architectures;
  • Hybrid energy storage for electrified aircraft;
  • Electrical machines for propulsion and for on-board power generation;
  • Power electronic converters for propulsion motors and for on-board power generation;
  • Electric power management, distribution, and protection;
  • Superconducting technologies (including cryogenic cooling systems);
  • Electrical system control, diagnostics, and health monitoring;
  • Fuel cell systems for propulsion and on-board power generation;
  • Hydrogen engine-based propulsion;
  • Power and propulsion system modeling and simulation;
  • Propulsion systems for eVTOL and flying cars;
  • Other impactful technologies.

Review papers may also be submitted.

Prof. Dr. Kaushik Rajashekara
Dr. Hao Huang
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. World Electric Vehicle Journal is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 1400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • electric aircraft
  • propulsion
  • distributed propulsion
  • flying cars
  • eVTOL
  • fuel cell
  • hybrid aircraft

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Further information on MDPI's Special Issue polices can be found here.

Published Papers (3 papers)

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Research

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17 pages, 2495 KiB  
Article
A Novel Method for Obtaining the Electrical Model of Lithium Batteries in a Fully Electric Ultralight Aircraft
by Jesús A. Salas-Cardona, José A. Posada-Montoya, Sergio D. Saldarriaga-Zuluaga, Nicolas Muñoz-Galeano and Jesús M. López-Lezama
World Electr. Veh. J. 2024, 15(11), 482; https://doi.org/10.3390/wevj15110482 - 23 Oct 2024
Viewed by 424
Abstract
This article introduces a novel approach for developing an electrical model of the lithium batteries used in an electric ultralight aircraft. Currently, no method exists in the technical literature for accurately modeling the electrical characteristics of batteries in an electric aircraft, making this [...] Read more.
This article introduces a novel approach for developing an electrical model of the lithium batteries used in an electric ultralight aircraft. Currently, no method exists in the technical literature for accurately modeling the electrical characteristics of batteries in an electric aircraft, making this study a valuable contribution to the field. The proposed method was validated with an all-electric ultralight aircraft designed and constructed at the Pascual Bravo University Institution. To build the detailed model, a kinematic analysis was first conducted through takeoff tests, where data on the speed, acceleration, time, and distance required for takeoff were collected, along with measurements of the current and power consumed by the batteries. The maximum speed and acceleration of the aircraft were also recorded. These kinematic results were obtained using two batteries made from Samsung INR-18650-35E lithium-ion cells, and different wing configurations of the aircraft were analyzed to assess their impacts on the battery energy consumption. Additionally, the discharge cycles of the batteries were evaluated. In the second phase, laboratory tests were performed on the individual battery cells, and the Peukert coefficient was estimated based on the experimental data. Finally, using the Peukert coefficient and the kinematic results from the takeoff tests, the electrical model of the battery was fine tuned. This model allows for the creation of charging and discharging equations for ultralight lithium batteries. With the final electrical model and energy consumption data during takeoff, it becomes possible to determine the energy usage and flight range of an electric aircraft. The model indicated that the aircraft did not require a long distance to takeoff, as it reached the necessary takeoff speed in a very short time. The equations used to simulate the discharge cycles of the batteries and lithium cells accurately described their energy capacities. Full article
(This article belongs to the Special Issue Electric and Hybrid Electric Aircraft Propulsion Systems)
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17 pages, 7488 KiB  
Article
Protection Coordination Strategy for the Distributed Electric Aircraft Propulsion Systems
by Anil Kumar Reddy Siddavatam, Kaushik Rajashekara, Hao Huang and Fred Wang
World Electr. Veh. J. 2024, 15(5), 187; https://doi.org/10.3390/wevj15050187 - 28 Apr 2024
Viewed by 991
Abstract
The current trend in distributed electric aircraft propulsion systems is to utilize the DC bus system at higher voltage levels than conventional aircraft systems. With Boeing and Airbus utilizing the +/−270 V bipolar DC bus system, the research on high-voltage systems is increasing [...] Read more.
The current trend in distributed electric aircraft propulsion systems is to utilize the DC bus system at higher voltage levels than conventional aircraft systems. With Boeing and Airbus utilizing the +/−270 V bipolar DC bus system, the research on high-voltage systems is increasing gradually, with voltage levels ranging from 1 to 10 kV systems or +/−0.5 to +/−5 kV DC bus systems. These voltage levels present considerable challenges to the distributed electric aircraft propulsion systems. In addition to partial discharge effects, there are other challenges, particularly the challenge associated with effectively limiting short-circuit fault currents due to the low cable impedance of the distribution system. The cable impedance is a significant factor that determines the fault current during fault conditions. Due to the low impedance, there is a sharp increase in fault current, necessitating an enhanced protection strategy, which ensures that the system is adequately protected. This paper introduces a coordinated protection strategy specifically designed for distributed electric aircraft propulsion systems to mitigate or prevent short-circuit faults. The proposed algorithm utilizes an I2t-based strategy and the current-limiting-based strategy to protect the system from short-circuit faults and overload conditions. Redundant backup protection is also included in the algorithm in case the circuit breaker fails to operate. Full article
(This article belongs to the Special Issue Electric and Hybrid Electric Aircraft Propulsion Systems)
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Review

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23 pages, 6853 KiB  
Review
Net-Zero Greenhouse Gas Emission Electrified Aircraft Propulsion for Large Commercial Transport
by Hao Huang and Kaushik Rajashekara
World Electr. Veh. J. 2024, 15(9), 411; https://doi.org/10.3390/wevj15090411 - 8 Sep 2024
Viewed by 737
Abstract
Until recently, electrified aircraft propulsion (EAP) technology development has been driven by the dual objectives of reducing greenhouse gas (GHG) emissions and addressing the depletion of fossil fuels. However, the increasing severity of climate change, posing a significant threat to all life forms, [...] Read more.
Until recently, electrified aircraft propulsion (EAP) technology development has been driven by the dual objectives of reducing greenhouse gas (GHG) emissions and addressing the depletion of fossil fuels. However, the increasing severity of climate change, posing a significant threat to all life forms, has resulted in the global consensus of achieving net-zero GHG emissions by 2050. This major shift has alerted the aviation electrification industry to consider the following: What is the clear path forward for EAP technology development to support the net-zero GHG goals for large commercial transport aviation? The purpose of this paper is to answer this question. After identifying four types of GHG emissions that should be used as metrics to measure the effectiveness of each technology for GHG reduction, the paper presents three significant categories of GHG reduction efforts regarding the engine, evaluates the potential of EAP technologies within each category as well as combinations of technologies among the different categories using the identified metrics, and thus determines the path forward to support the net-zero GHG objective. Specifically, the paper underscores the need for the aviation electrification industry to adapt, adjust, and integrate its EAP technology development into the emerging new engine classes. These innovations and collaborations are crucial to accelerate net-zero GHG efforts effectively. Full article
(This article belongs to the Special Issue Electric and Hybrid Electric Aircraft Propulsion Systems)
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