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Electric-Powered and Hybrid-Powered Unmanned Aerial Vehicle Technology and Applications of...
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Electric-Powered and Hybrid-Powered Unmanned Aerial Vehicle Technology and Applications of Low Altitude Aviation

A special issue of Drones (ISSN 2504-446X). This special issue belongs to the section "Innovative Urban Mobility".

Deadline for manuscript submissions: 30 September 2025 | Viewed by 4007

Special Issue Editors

Dr. Wenbiao Gan

E-Mail Website
Guest Editor
Institute of Unmanned System, Beihang University, Beijing, China
Interests: UAV; aerospace engineering; aerodynamics; low altitude aviation; distributed power design
Dr. Zhou Zhou

E-Mail Website
Guest Editor
College of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China,School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China
Interests: UAV system overall, UAV overall layout, UAV aerodynamic layout and design, UAV flight mechanics and control, UAV airworthiness and verification, intelligent UAV comprehensive design
Dr. Saddam Aziz

E-Mail Website
Guest Editor
Department of Electrical and Electronic Engineering, The Hong Kong Polytechnic University, Hong Kong
Interests: renewable energy integration; cyber-physical power system; artificial intelligence
Special Issues, Collections and Topics in MDPI journals
Dr. Ilias Panagiotopoulos

E-Mail Website
Guest Editor
Department of Informatics and Telematics, Harokopio University of Athens, 17778 Athens, Greece
Interests: aerospace Engineering; unmanned aerial vehicles; exterior ballistics; intelligent transportation systems

Special Issue Information

Dear Colleagues,

Electric-Powered unmanned aerial vehicles(UAVs) play an important role in promoting low altitude aviation and economy development. We are happy to announce a Special Issue entitled "Electric-Powered Unmanned Aerial Vehicle Technology Technology and Applications of Low Altitude Aviation". This Special Issue will complete a group of international papers published in the field of Electric-Powered UAV technology and low altitude aviation, with its rapid growth in popularity anticipated.Currently, new electric-powered UAV technology technology and low Altitude aviation systems are in an era of transformation. Technology development involves the development of modeling, simulation, aerodynamic and flight dynamic analysis of electric UAV. New technology hotspots are developing rapidly, including distributed electric power, eVOTL and low altitude solar-powered UAV. Some application topics deserve more attention, such as artificial intelligence technology，urban air mobility and delivery，Low altitude economy analysis by electric-powered aircraft, et al.This Special Issue aims to collect new developments and emerging technologies in the field of Electric-Powered UAV technology and applications with reviews, regular research papers, communications, and short notes. We encourage submissions which provide the community with the most recent advancements in all aspects of Electric-Powered UAV, including but not limited to:

  1. Modeling and simulation of new aircraft configurations;
  2. Aerodynamic and flight dynamic analysis of new aircraft;
  3. Development and application of Electric-Powered UAV;
  4. Distributed electric power design and analysis for UAV;
  5. Design and dynamic analysis of eVOTL;
  6. Design and performance analysis of multi-rotor UAV
  7. Design and dynamic analysis of low altitude solar-powered UAV;
  8. Design and performance analysis of micro and small logistics UAV
  9. Artificial intelligence technology of electric-powered UAV system;
  10. Urban air mobility and delivery by electric-powered aircraft;
  11. Green Aviation Technology;
  12. Low altitude aviation and economy analysis

We look forward to your contributions.

Dr. Wenbiao Gan
Dr. Zhou Zhou
Dr. Saddam Aziz
Dr. Ilias Panagiotopoulos
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. Drones 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 2600 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-powered aircraft
  • distributed power
  • UAV
  • optimization design
  • aerodynamics
  • artificial intelligence
  • green aviation
  • urban air mobility and delivery
  • low altitude economy

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

Published Papers (6 papers)

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Research

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22 pages, 6550 KiB  
Article
Research on Conceptual Design Method and Propulsive/Aerodynamic Coupling Characteristics of DEP STOL UAV
by Xin Zhao, Zhou Zhou, Kelei Wang, Han Wang and Xu Li
Drones 2025, 9(5), 363; https://doi.org/10.3390/drones9050363 - 11 May 2025
Viewed by 209
Abstract
This paper establishes an analytical model for component mass, takeoff weight, and performance constraints of distributed electric propulsion (DEP) propeller-driven short takeoff and landing (STOL) unmanned aerial vehicles (UAV), and develops a conceptual design method considering propulsive/aerodynamic coupling effects. The proposed approach was [...] Read more.
This paper establishes an analytical model for component mass, takeoff weight, and performance constraints of distributed electric propulsion (DEP) propeller-driven short takeoff and landing (STOL) unmanned aerial vehicles (UAV), and develops a conceptual design method considering propulsive/aerodynamic coupling effects. The proposed approach was applied to design a 350 kilogram-class DEP UAV with STOL capability, verifying the feasibility and effectiveness of the design method. To investigate the layout design and propulsive/aerodynamic coupling characteristics of DEP UAV, three UAV configurations with different DEP arrangements are formulated and studied, and the results indicate that the flap deflection significantly increases the lift coefficient of the UAV during takeoff, and under the same total thrust and power conditions, the lift-enhancement using DEP arrangement is more significant. In addition, it is necessary to fully consider the propulsive/aerodynamic coupling effects in the conceptual design process, and this is of great significance for the future development of DEP STOL UAV. Full article
(This article belongs to the Special Issue Electric-Powered and Hybrid-Powered Unmanned Aerial Vehicle Technology and Applications of Low Altitude Aviation)
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14 pages, 10151 KiB  
Article
Evaluation of Aerodynamic Performance of a Multi-Rotor eVTOL During Landing Using the Lattice Boltzmann Method
by Menglong Ding, Huadong Li, Lintao Shao, Jinting Xuan, Chuanyan Feng, Xufei Yan and Dawei Bie
Drones 2025, 9(5), 332; https://doi.org/10.3390/drones9050332 - 25 Apr 2025
Viewed by 309
Abstract
Electric vertical take-off and landing (eVTOL) aircraft are transforming urban air mobility (UAM) by providing efficient, low-emission, and rapid transit in congested cities. However, ensuring safe and stable landings remains a critical challenge, particularly in constrained urban environments with variable wind conditions. This [...] Read more.
Electric vertical take-off and landing (eVTOL) aircraft are transforming urban air mobility (UAM) by providing efficient, low-emission, and rapid transit in congested cities. However, ensuring safe and stable landings remains a critical challenge, particularly in constrained urban environments with variable wind conditions. This study investigates the landing aerodynamics of a multi-rotor eVTOL using the lattice Boltzmann method (LBM), a computational approach well-suited to complex boundary conditions and parallel processing. This analysis examines the ground effect, descent speed, and crosswind influence on lift distribution and stability. A rooftop landing scenario is also explored, where half of the rotors operate over a rooftop while the rest remain suspended in open air. Results indicate that rooftop landings introduce asymmetric lift distribution due to crosswind and roof-induced flow circulation, significantly increasing rolling moment compared to ground landings. These findings underscore the role of descent speed, crosswinds, and landing surface geometry in eVTOL aerodynamics, particularly the heightened risk of rollover in rooftop scenarios. Full article
(This article belongs to the Special Issue Electric-Powered and Hybrid-Powered Unmanned Aerial Vehicle Technology and Applications of Low Altitude Aviation)
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23 pages, 10074 KiB  
Article
Drone Electric Propulsion System with Hybrid Power Source
by Jenica-Ileana Corcau, Liviu Dinca, Andra-Adelina Cucu and Dmitrii Condrea
Drones 2025, 9(4), 301; https://doi.org/10.3390/drones9040301 - 11 Apr 2025
Viewed by 558
Abstract
Unmanned aerial vehicles, known today as drones, in the beginning, were small-dimension research models powered by small electric motors fed from electrical batteries. The propulsion system for these drones had to be adapted to the specific applications along their development. Electric and hybrid-electric [...] Read more.
Unmanned aerial vehicles, known today as drones, in the beginning, were small-dimension research models powered by small electric motors fed from electrical batteries. The propulsion system for these drones had to be adapted to the specific applications along their development. Electric and hybrid-electric propulsion drones represent a rapidly developing field in the aerospace industry. Electric drones are those with purely electric propulsion fed from batteries, while hybrid-electric ones have a hybrid propulsion system combining a thermal engine and an electric motor. Another class of hybrid-electric drones includes those with an electric propulsion system fed from fuel cells and batteries. This paper proposes the configuration of an electric propulsion system with a hybrid power source for a transport drone, as well as an analysis of the special electrical components onboard an electric drone, such as batteries, fuel cells, and electric motors. In the final part of the paper, this propulsion system is modeled and analyzed in Matlab/Simulink version 2021a. Design software and simulation tools specifically developed for hybrid-electric drones are essential for ensuring the accuracy and efficiency of these processes. Electric drones have the advantage of zero emissions, but at present, the batteries are still too heavy for aviation applications. By using hydrogen fuel cells as the main power source, it is possible to considerably reduce the power source weight. This is an important advantage of the system proposed in this work. Using hydrogen fuel cells in aircraft and drone propulsion is an important trend in the scientific world. This technology seems to be mature enough to be implemented in aviation. From a technical point of view, these kinds of systems are already feasible. Their usefulness and reliability have to be proven in time. Full article
(This article belongs to the Special Issue Electric-Powered and Hybrid-Powered Unmanned Aerial Vehicle Technology and Applications of Low Altitude Aviation)
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40 pages, 16671 KiB  
Article
Multi-Mode Flight Simulation and Energy-Aware Coverage Path Planning for a Lift+Cruise QuadPlane
by Akshay Mathur and Ella Atkins
Drones 2025, 9(4), 287; https://doi.org/10.3390/drones9040287 - 8 Apr 2025
Cited by 1 | Viewed by 320
Abstract
This paper describes flight planning supported by modeling, guidance, and feedback control for an electric Vertical Take-Off and Landing (eVTOL) QuadPlane small Uncrewed Aircraft System (sUAS). Five Lift+Cruise sUAS waypoint types are defined and used to construct smooth flight path geometries and acceleration [...] Read more.
This paper describes flight planning supported by modeling, guidance, and feedback control for an electric Vertical Take-Off and Landing (eVTOL) QuadPlane small Uncrewed Aircraft System (sUAS). Five Lift+Cruise sUAS waypoint types are defined and used to construct smooth flight path geometries and acceleration profiles. Novel accelerated coverage flight plan segments for hover (Lift) and coverage (Cruise) waypoint types are defined as a complement to traditional fly-over, fly-by, and Dubins path waypoint transit solutions. Carrot-chasing guidance shows a tradeoff between tracking accuracy and control stability as a function of the carrot time step. Experimentally validated aerodynamic and thrust models for vertical, forward, and hybrid flight modes are developed as a function of airspeed and angle of attack from wind tunnel data. A QuadPlane feedback controller augments classical multicopter and fixed-wing controllers with a hybrid control mode that combines multicopter and aircraft control actuators to add a controllable pitch degree of freedom at the cost of increased energy use. Multi-mode flight simulations show Cruise mode to be the most energy efficient with a relatively large turning radius constraint, while quadrotor mode enables hover and smaller radius turns. Energy efficiency analysis over QuadPlane plans with modest inter-waypoint distances indicates cruise or aircraft mode is 30% more energy efficient overall than quadrotor mode. Energy-aware coverage planner simulation results show fly-coverage (cruise) waypoints are always the most efficient given long distances between waypoints. A Pareto analysis of energy use versus area coverage is presented to analyze waypoint-type tradeoffs in case studies with closely spaced waypoints. Coverage planning and guidance methods from this paper can be applied to any Lift+Cruise aircraft configuration requiring waypoint flight mode optimization over energy and coverage metrics. Full article
(This article belongs to the Special Issue Electric-Powered and Hybrid-Powered Unmanned Aerial Vehicle Technology and Applications of Low Altitude Aviation)
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23 pages, 6441 KiB  
Article
Aerodynamic Investigation for a Propeller-Induced Lift-Enhancing Vertical Take-Off and Landing (VTOL) Configuration
by Hongbo Wang, Guangjia Li, Jie Li and Junjie Zhuang
Drones 2025, 9(1), 20; https://doi.org/10.3390/drones9010020 - 29 Dec 2024
Viewed by 761
Abstract
Difficulty in thrust-matching between the cruise and vertical take-off and landing (VTOL) phases is one of the prominent issues faced by conventional VTOL fixed-wing drones. To address this issue, a propeller-induced lift-enhancing (PILE) biplane wing VTOL configuration is proposed with the goal of [...] Read more.
Difficulty in thrust-matching between the cruise and vertical take-off and landing (VTOL) phases is one of the prominent issues faced by conventional VTOL fixed-wing drones. To address this issue, a propeller-induced lift-enhancing (PILE) biplane wing VTOL configuration is proposed with the goal of lift enhancement on the wing during the no-forward-speed VTOL phase. Numerical simulation methods are used to study and analyze the aerodynamic characteristics of this configuration in the cruise and VTOL phases. The results show that the favorable inducing effect of the propeller makes the PILE configuration have a good effect of increasing lift and reducing drag compared with a single wing of the same area during the cruise phase, improving the lift-to-drag ratio by 7.27%. During the VTOL phase, the optimal tilt angle of the propeller for the PALE configuration is 70°, matched with an installation angle of 5° for the aided wing. This parameter combination balances the total drag while also achieving a lift-to-thrust ratio of 1.12. As a result, the required thrust of the propeller is reduced under the same take-off weight, which helps to alleviate the thrust-matching problem and enables VTOL with a smaller power cost. Full article
(This article belongs to the Special Issue Electric-Powered and Hybrid-Powered Unmanned Aerial Vehicle Technology and Applications of Low Altitude Aviation)
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Review

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18 pages, 5874 KiB  
Review
Key Technology for Human-System Integration of Unmanned Aircraft Systems in Urban Air Transportation
by Chuanyan Feng, Jinwei Hou, Shuang Liu, Xiaoru Wanyan, Menglong Ding, Huadong Li, De Yan and Dawei Bie
Drones 2025, 9(1), 18; https://doi.org/10.3390/drones9010018 - 27 Dec 2024
Cited by 1 | Viewed by 922
Abstract
Effective integration of human factors and systems engineering has become a technical challenge that constrains the full realization of human performance in unmanned aircraft systems (UAS) for urban air transportation. To address this challenge, breakthroughs are needed in key technologies related to human-system [...] Read more.
Effective integration of human factors and systems engineering has become a technical challenge that constrains the full realization of human performance in unmanned aircraft systems (UAS) for urban air transportation. To address this challenge, breakthroughs are needed in key technologies related to human-system integration (HSI) of UAS. Based on literature review and industry practices, unique HF challenges of UAS are identified, and two research issues, HSI analysis throughout UAS development lifecycle and HSI practice under UAS typical lifecycle stages, are summarized. To address these issues, a model-based human-system integration (MBHSI) design framework is proposed for the UAS development lifecycle, along with an HSI practice framework for UAS under typical human readiness levels. The HSI design and practice framework can provide references for HF design of UAS in urban air transportation. Full article
(This article belongs to the Special Issue Electric-Powered and Hybrid-Powered Unmanned Aerial Vehicle Technology and Applications of Low Altitude Aviation)
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