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Aerospace
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Advances in UAVs: Design Methods, Performance Enhancement Techniques and Technologies
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Advances in UAVs: Design Methods, Performance Enhancement Techniques and Technologies

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

Deadline for manuscript submissions: 15 July 2026 | Viewed by 6876

Special Issue Editor

Dr. Pericles Panagiotou

E-Mail Website
Guest Editor
Laboratory of Fluid Mechanics and Turbomachinery, School of Mechanical Engineering, Aristotle University of Thessaloniki, Thessaloniki, Greece
Interests: aircraft design; fixed-wing UAVs; applied aerodynamics; CFD; wind tunnel experiments

Special Issue Information

Dear Colleagues,

This Special Issue is dedicated to one of the most rapidly advancing fields of modern aviation—Unmanned Aerial Vehicles. These range from small-scale aerial vehicles that weigh a few kilograms to large platforms with a GTOW of several tonnes; they can conduct several missions at an increased effectiveness and efficiency compared to crewed aircraft. In the 21st century, UAVs have established a presence in global aviation, which, in turn, has led to a substantial increase in dedicated research studies and projects by academia and industry alike. Authors are invited to present their research on UAV-related topics, focused on (but not limited to) the following:

  • Layout design and aerodynamics;
  • Flow control techniques;
  • Alternative energy sources and energy methods;
  • Structures and materials;
  • Airworthiness;
  • Sensors.

Dr. Pericles Panagiotou
Guest Editor

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 250 words) can be sent to the Editorial Office for assessment.

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

  • UAVs
  • design and synthesis
  • innovative layouts
  • aerodynamics
  • optimization
  • flow control
  • alternative energy sources
  • solar energy
  • flight planning
  • structures
  • materials
  • airworthiness

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

Published Papers (7 papers)

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Research

18 pages, 2482 KB  
Article
Analysis and Enhancement of Steady Climb Performance with Control Input Redundancy for a Dual-Propulsion VTOL UAV
by Chihiro Kikumoto, Takateru Urakubo, Kohtaro Sabe and Yuichi Hazama
Aerospace 2026, 13(4), 316; https://doi.org/10.3390/aerospace13040316 - 28 Mar 2026
Viewed by 264
Abstract
Dual-propulsion UAVs employ separate rotors for rotary-wing and fixed-wing modes to achieve VTOL (vertical take-off and landing) and high-speed cruise. This paper analyzes steady climb in high-speed flight by utilizing the redundant rotary-wing rotors. We develop the models of aerodynamic forces and thrust [...] Read more.
Dual-propulsion UAVs employ separate rotors for rotary-wing and fixed-wing modes to achieve VTOL (vertical take-off and landing) and high-speed cruise. This paper analyzes steady climb in high-speed flight by utilizing the redundant rotary-wing rotors. We develop the models of aerodynamic forces and thrust forces of a dual-propulsion UAV to obtain its longitudinal dynamic model. The maneuverability of the UAV is analyzed based on the dynamic model to reveal whether a steady climb at a given climb angle is possible within allowable thrust forces. The analytical results show that the climb flight performance of the UAV can be enhanced by utilizing the redundant control inputs during high-speed flights. Flight experiments not only demonstrate that several climb flight states predicted by the analysis are successfully realized, but also that steady climb at a higher climb angle, unattainable in conventional fixed-wing mode, is made possible by simultaneously using the rotors for rotary-wing mode. The enhanced flight performance would increase the number of missions that the UAV can accomplish. Full article
(This article belongs to the Special Issue Advances in UAVs: Design Methods, Performance Enhancement Techniques and Technologies)
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41 pages, 13373 KB  
Article
Experimental Validation of a Stepwise Automatic Determination Method for TECS Parameters in ArduPilot Based on Steady-State Assessment
by Ryoya Fukada, Kazuaki Hatanaka and Mitsutomo Hirota
Aerospace 2026, 13(2), 193; https://doi.org/10.3390/aerospace13020193 - 17 Feb 2026
Viewed by 1013
Abstract
We propose a stepwise in-flight method for automatically determining flight-envelope-related parameters for the longitudinal control of small fixed-wing unmanned aerial vehicles (UAVs), including pitch-angle limits, maximum climb and sink rate limits, and the cruise (trim) throttle. The method performs steady-state evaluation using onboard [...] Read more.
We propose a stepwise in-flight method for automatically determining flight-envelope-related parameters for the longitudinal control of small fixed-wing unmanned aerial vehicles (UAVs), including pitch-angle limits, maximum climb and sink rate limits, and the cruise (trim) throttle. The method performs steady-state evaluation using onboard state estimates and sequentially updates the parameter set of ArduPilot’s energy-based longitudinal controller (Total Energy Control System, TECS). The algorithm was implemented in ArduPilot Plane v4.6.1 via Lua scripting, enabling real-time parameter determination and immediate application during flight. The proposed procedure was assessed in software-in-the-loop (SITL) simulations and further validated through flight experiments. The results demonstrated that the target parameters could be automatically identified during flight and implemented in real time. The proposed method is expected to reduce reliance on expert trial-and-error and contribute to improving portability across airframes and configuration changes. Full article
(This article belongs to the Special Issue Advances in UAVs: Design Methods, Performance Enhancement Techniques and Technologies)
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16 pages, 3343 KB  
Article
Experimental Evaluation of Energy Consumption and Acoustic Emissions in Sub-250 g Quadcopters with Added Tubular Propeller Enclosures
by Mateusz Woźniak, Paweł Bury and Artur Kierzkowski
Aerospace 2026, 13(2), 182; https://doi.org/10.3390/aerospace13020182 - 13 Feb 2026
Viewed by 430
Abstract
This paper investigates the impact of tubed propeller design on the energy efficiency and acoustic emissions of sub-250 g quadcopters. This study was motivated by the growing popularity of ultralight UAVs and the lack of experimental data addressing the trade-offs between noise, efficiency, [...] Read more.
This paper investigates the impact of tubed propeller design on the energy efficiency and acoustic emissions of sub-250 g quadcopters. This study was motivated by the growing popularity of ultralight UAVs and the lack of experimental data addressing the trade-offs between noise, efficiency, and mass. Ten drone configurations with varying tube geometries and tip clearances were constructed using 3D-printed PLA+ frames and identical propulsion components. Experimental tests were conducted in a reverberation room to measure sound pressure levels and onboard energy consumption during hover. The results show that tubed configurations are 3–6.5 dB louder than untubed ones, with a noticeable shift toward higher frequencies. While tubes increased total power demand by 18–37% compared to the lightest design, they also reduced it by 3–17% relative to untubed drones of the same mass. The findings demonstrate that tubing improves aerodynamic efficiency only under same mass constraints and is most beneficial when mechanical protection is prioritized over noise and endurance. Full article
(This article belongs to the Special Issue Advances in UAVs: Design Methods, Performance Enhancement Techniques and Technologies)
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24 pages, 6265 KB  
Article
On the Study of Performance Enhancement of 3D Printing and Industrial Application on Aviation Devices
by Hui-Pei Chang and Yung-Lan Yeh
Aerospace 2026, 13(1), 90; https://doi.org/10.3390/aerospace13010090 - 14 Jan 2026
Viewed by 419
Abstract
Three-dimensional printing is the most commonly used method for producing customized or mock-up products for industrial applications. In particular, aviation devices for drones usually require a high spatial resolution to satisfy the small size requirement. In practical applications of drones, the two main [...] Read more.
Three-dimensional printing is the most commonly used method for producing customized or mock-up products for industrial applications. In particular, aviation devices for drones usually require a high spatial resolution to satisfy the small size requirement. In practical applications of drones, the two main tasks are inspection and detection. However, the working environment is often filled with flammable gases, such as natural gas or petroleum gas. Thus, the parts of drones that can easily produce an electrical spark, such as electronic connectors, should be specially protected. In this study, atmosphere control was applied to enhance the printing performance and manufacture of anti-explosion devices. The results demonstrate that atmosphere control can efficiently improve the print quality and that the print resolution of a commercial 3D printer can be enhanced to reach the mm scale. In the anti-pressure testing via a high-pressure smoke experiment, the manufactured anti-explosion devices for drones showed an appropriate intrinsic safety level, suggesting that they can be used in drones used for daily inspections of pipelines in petrochemical plants. The two main contributions of this study are the development of a practical method for improving FDM 3D printers and an anti-explosion device for drones. Full article
(This article belongs to the Special Issue Advances in UAVs: Design Methods, Performance Enhancement Techniques and Technologies)
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16 pages, 3885 KB  
Article
Design and Evaluation of an Additively Manufactured UAV Fixed-Wing Using Gradient Thickness TPMS Structure and Various Shells and Infill Micro-Porosities
by Georgios Moysiadis, Savvas Koltsakidis, Odysseas Ziogas, Pericles Panagiotou and Dimitrios Tzetzis
Aerospace 2026, 13(1), 50; https://doi.org/10.3390/aerospace13010050 - 2 Jan 2026
Cited by 2 | Viewed by 1049
Abstract
Unmanned Aerial Vehicles (UAVs) have become indispensable tools, playing a pivotal role in diverse applications such as rescue missions, agricultural surveying, and air defense. They significantly reduce operational costs while enhancing operator safety, enabling new strategies across multiple domains. The growing demand for [...] Read more.
Unmanned Aerial Vehicles (UAVs) have become indispensable tools, playing a pivotal role in diverse applications such as rescue missions, agricultural surveying, and air defense. They significantly reduce operational costs while enhancing operator safety, enabling new strategies across multiple domains. The growing demand for UAVs calls for structural components that are not only robust and lightweight, but also cost-efficient. This research introduces a novel approach that employs a pressure distribution map on the external surface of a UAV wing to optimize its internal structure through a variable-thickness TPMS (Triply Periodic Minimal Surface) design. Beyond structural optimization, the study explores a second novel approach with the use of filaments containing chemical blowing agents printed at different temperatures for both the infill and shell, producing varying porosities. As a result, the tailoring of density and weight is achieved through two different methods, and case studies were developed by combining them. Compared to the conventionally manufactured wing, a weight reduction of up to 7% was achieved while the wing could handle the aerodynamic loads under extreme conditions. Beyond enabling lightweight structures, the process has the potential to be substantially faster and more cost-effective, eliminating the need for molds and advanced composite materials such as carbon fiber sheets. Full article
(This article belongs to the Special Issue Advances in UAVs: Design Methods, Performance Enhancement Techniques and Technologies)
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27 pages, 59170 KB  
Article
Effects of Vectorial Inflow on the Multi-Axis Aerodynamic Performance of a Small-Sized UAV Rotor
by Cong Liu, Yu Wang and Zhiqiang Wei
Aerospace 2025, 12(12), 1096; https://doi.org/10.3390/aerospace12121096 - 10 Dec 2025
Cited by 1 | Viewed by 773
Abstract
Variations in flight trajectory and velocity during vertical takeoff, transition, and level flight cause substantial changes in the relative inflow vector of multi-rotor unmanned aerial vehicles (UAVs). In urban environments, disturbances from complex wind fields further increase the uncertainty of inflow conditions. This [...] Read more.
Variations in flight trajectory and velocity during vertical takeoff, transition, and level flight cause substantial changes in the relative inflow vector of multi-rotor unmanned aerial vehicles (UAVs). In urban environments, disturbances from complex wind fields further increase the uncertainty of inflow conditions. This study investigates the aerodynamic characteristics of a fixed-pitch small-sized UAV rotor under varying inflow angles, velocities, and rotational speeds using a subsonic return-flow wind tunnel. The experimental setup enables inflow angle control from −90° to +90° via a turntable. Results indicate that, without incoming flow, the axial thrust and torque coefficients remain nearly constant. With inflow, both coefficients become highly sensitive to velocity in the 2000–5000 rpm range, with deviations up to four times those under static conditions. The in-plane lateral force along the X-axis increases significantly with inflow velocity, reaching about half the axial force, while the Y-axis component is minor and negligible under symmetric configurations. Pitching and rolling moments increase rapidly once inflow velocity exceeds 8 m/s, surpassing the axial torque and exhibiting strong directional asymmetry around ±15° inflow angles. The results demonstrate coupled aerodynamic force and moment behavior of small rotors under complex inflow, providing experimental evidence for improved dynamic modeling, control design, and the energy optimization of UAVs operating in turbulent wind environments. Full article
(This article belongs to the Special Issue Advances in UAVs: Design Methods, Performance Enhancement Techniques and Technologies)
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22 pages, 5146 KB  
Article
Improving Control Performance of Tilt-Rotor VTOL UAV with Model-Based Reward and Multi-Agent Reinforcement Learning
by Muammer Ugur and Aydin Yesildirek
Aerospace 2025, 12(9), 814; https://doi.org/10.3390/aerospace12090814 - 9 Sep 2025
Cited by 1 | Viewed by 2093
Abstract
Tilt-rotor Vertical Takeoff and Landing Unmanned Aerial Vehicles (TR-VTOL UAVs) combine fixed-wing and rotary-wing configurations, offering optimized flight planning but presenting challenges due to their complex dynamics and uncertainties. This study investigates a multi-agent reinforcement learning (RL) control system utilizing Soft Actor-Critic (SAC) [...] Read more.
Tilt-rotor Vertical Takeoff and Landing Unmanned Aerial Vehicles (TR-VTOL UAVs) combine fixed-wing and rotary-wing configurations, offering optimized flight planning but presenting challenges due to their complex dynamics and uncertainties. This study investigates a multi-agent reinforcement learning (RL) control system utilizing Soft Actor-Critic (SAC) modules, which are designed to independently control each input with a tailored reward mechanism. By implementing a novel reward structure based on a dynamic reference response region, the multi-agent design improves learning efficiency by minimizing data redundancy. Compared to other control methods such as Actor-Critic Neural Networks (AC NN), Proximal Policy Optimization (PPO), Nonsingular Terminal Sliding Mode Control (NTSMC), and PID controllers, the proposed system shows at least a 30% improvement in transient performance metrics—including RMSE, rise time, settling time, and maximum overshoot—under both no wind and constant 20 m/s wind conditions, representing an extreme scenario to evaluate controller robustness. This approach has also reduced training time by 80% compared to single-agent systems, lowering energy consumption and environmental impact. Full article
(This article belongs to the Special Issue Advances in UAVs: Design Methods, Performance Enhancement Techniques and Technologies)
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