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Aerospace
Special Issues
Aircraft Electric Power System: Design, Control, and Maintenance
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Aircraft Electric Power System: Design, Control, and Maintenance

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: 31 March 2025 | Viewed by 2952

Special Issue Editors

Dr. Yuan Gao

E-Mail Website
Guest Editor
School of Engineering, University of Leicester, Leicester LE1 7RH, UK
Interests: model predictive control; power electronics; motor drive control; machine learning; artificial intelligence
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Shoujun Song

E-Mail Website
Guest Editor
School of Automation, Northwestern Polytechnical University, Xi’an 710072, China
Interests: machine control; model predictive control; electric aircraft; power conversion; permanent magnet synchronous motor
Prof. Dr. Pat Wheeler

E-Mail Website
Guest Editor
Department of Electrical and Electronic Engineering, Faculty of Engineering, University of Nottingham, Nottingham NG7 2RD, UK
Interests: power electronics; matrix converters; multi-level converters/multi-cellular converters; more electric aircraft
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The development of electrical power systems (EPS) for more-electric, hybrid-electric, and all-electric aircrafts represents a significant shift in aviation technology, driven by aims of higher efficiency, greener aviation, and improved efficiency and reliability. This shift integrates versatile electrical onboard systems/components that were traditionally powered by hydraulic, mechanical, or pneumatic power sources

Electrical power systems for aircraft is a growing, multidisciplinary research field which encompasses aspects of electrical engineering, systems engineering, control theory, and aerospace engineering to ensure that modern aircrafts can efficiently generate, distribute, and utilize electrical power. The key components and technologies include generation systems, power distribution, energy storage, control systems, load management, etc. Tackling the challenges in this field (e.g., thermal management, battery technology, system integration, infrastructure for charging and maintenance) requires advanced technologies (for example, artificial intelligence, digital twin) to further enhance the system efficiency, reduce the weight/space/cost of electrical components, and ensure high reliability and safety standards.

The development of electrical power systems for more-electric, hybrid-electric, and all-electric aircrafts is paving the way for the future of aviation. This Special Issue aims to provide a platform for international researchers in academia and industry to share their contributions to the fields of aircraft electric power system design, control, and maintenance.

Dr. Yuan Gao
Prof. Dr. Shoujun Song
Prof. Dr. Pat Wheeler
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. Aerospace 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 2400 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

  • electrical power system
  • more-electric aircraft
  • hybrid-electric aircraft
  • all-electric aircraft
  • motor drive system
  • power converters
  • machine design and control
  • energy management
  • fault detection and diagnostics of power system
  • microgrid onboard aircraft

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Published Papers (3 papers)

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26 pages, 7066 KiB  
Article
Comprehensive Thermodynamic Performance Evaluation of a Novel Dual-Shaft Solid Oxide Fuel Cell Hybrid Propulsion System
by Jinghui Xu, Xizhen Wang, Zepeng Wang, Kaiqiang Yang, Xueshun Li and Yongjun Zhao
Aerospace 2025, 12(1), 59; https://doi.org/10.3390/aerospace12010059 - 16 Jan 2025
Viewed by 514
Abstract
With the rapid growth of air travel, reducing carbon emissions in aviation is imperative. Electric aircraft play a key role in achieving sustainable aviation, especially for large civil aircraft, where reducing emissions, improving the fuel efficiency, and enabling flexible power regulation are essential. [...] Read more.
With the rapid growth of air travel, reducing carbon emissions in aviation is imperative. Electric aircraft play a key role in achieving sustainable aviation, especially for large civil aircraft, where reducing emissions, improving the fuel efficiency, and enabling flexible power regulation are essential. This study proposes a dual-shaft, separated-exhaust fuel cell hybrid aircraft propulsion system (HAPS), using a solid oxide fuel cell (SOFC) to replace the conventional turbine-driven compressor. The independent speed control of the high- and low-pressure spools is realized via a power distribution system. A thermodynamic model is developed, and performance evaluations, including parametric, exergy, and sensitivity analyses, are conducted. At the design point, the system delivers 36.304 kN thrust, 16.775 g/(kN·s) specific fuel consumption, 15.931 MW SOFC power, and 54.759% SOFC efficiency. The exergy analysis highlights the optimization of components like the heat exchanger and fan to reduce energy losses. The sensitivity analysis reveals that the spool speeds and fuel utilization significantly impact the performance. The findings provide valuable insights into optimizing control strategies and offer a novel, efficient, and low-carbon power solution for aviation, supporting the industry’s transition towards sustainability. Full article
(This article belongs to the Special Issue Aircraft Electric Power System: Design, Control, and Maintenance)
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18 pages, 15534 KiB  
Article
A Data-Driven Feature Extraction Process of Interleaved DC/DC Converter Due to the Degradation of the Capacitor in the Aircraft Electrical System
by Chenguang Zhang, Pengfei Gao, Ming Huang, Wenjie Liu, Weilin Li and Xiaobin Zhang
Aerospace 2024, 11(12), 1027; https://doi.org/10.3390/aerospace11121027 - 16 Dec 2024
Viewed by 512
Abstract
In recent years, preventive maintenance has emerged as a focal point of research in the aerospace field. The concept of equipment maintenance, exemplified by prognosis and health management (PHM), has permeated every aspect of development and design. Extracting degradation features presents a fundamental [...] Read more.
In recent years, preventive maintenance has emerged as a focal point of research in the aerospace field. The concept of equipment maintenance, exemplified by prognosis and health management (PHM), has permeated every aspect of development and design. Extracting degradation features presents a fundamental and challenging task for health assessment and remaining useful life prediction. To facilitate the efficient operation of the incipient fault diagnosis model, this paper proposes a data-driven feature extraction process for converters, which consists of two main stages. First, feature extraction and comparison are conducted in the time domain, frequency domain, and time–frequency domain. By employing wavelet decomposition and the Hilbert transform method, a highly correlated time–frequency domain feature is obtained. Second, an improved feature selection approach that combines the ReliefF algorithm with the correlation coefficient is proposed to effectively minimize redundancy within the feature subset. Furthermore, an incipient fault diagnosis model is established using neural networks, which verifies the effectiveness of the data-driven feature extraction process presented herein. Experimental results indicate that this method not only maintains fault diagnosis accuracy but also significantly reduces training time. Full article
(This article belongs to the Special Issue Aircraft Electric Power System: Design, Control, and Maintenance)
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22 pages, 13437 KiB  
Article
A Novel Approach to Ripple Cancellation for Low-Speed Direct-Drive Servo in Aerospace Applications
by Xin Zhang, Ziting Wang, Chaoping Bai and Shuai Zhang
Aerospace 2024, 11(10), 834; https://doi.org/10.3390/aerospace11100834 - 10 Oct 2024
Viewed by 912
Abstract
Low-frequency harmonic interference is an important factor that affects the performance of low-speed direct-drive servo systems. In order to improve the low-speed smoothness of direct-drive servo, firstly, the causes of the first and second harmonics of electromagnetic torque and tooth harmonics are analyzed [...] Read more.
Low-frequency harmonic interference is an important factor that affects the performance of low-speed direct-drive servo systems. In order to improve the low-speed smoothness of direct-drive servo, firstly, the causes of the first and second harmonics of electromagnetic torque and tooth harmonics are analyzed based on the mathematical model of PMSM (permanent magnet synchronous motor) and the principle of vector control. Accordingly, the CC-EUMA (Electrical angle Update and Mechanical angle Assignment algorithm for Center Current) and SL-DQPR (Double Quasi-Proportional Resonant control algorithm for Speed Loop) algorithm are proposed. Second, to confirm the algorithm’s efficacy, the harmonic environment is simulated using Matlab/Simulink, and the built harmonic suppression module is simulated and analyzed. Then, a miniaturized, fully digital drive control system is built based on the architecture of the Zynq-7000 series chips. Finally, the proposed suppression algorithm is verified at the board level. According to the experimental results, the speed ripple decreases to roughly one-third of its initial value after the algorithm is included. This effectively delays the speed ripple’s low-speed deterioration and provides a new idea for the low-speed control of the space direct-drive servo system. Full article
(This article belongs to the Special Issue Aircraft Electric Power System: Design, Control, and Maintenance)
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