Topic Editors

Institute of Mechanical Engineering, Faculty of Mechanical Engineering, Bialystok University of Technology, 15-351 Bialystok, Poland
Department of Aerospace Engineering, Faculty of Engineering, University Putra Malaysia, Serdang 43400, Selangor Darul Ehsan, Malaysia
School of Electrical and Data Engineering, University of Technology Sydney, Ultimo 2007, NSW, Australia
Institute of Robotics and Machine Intelligence, Faculty of Control, Robotics and Electrical Engineering, Poznan University of Technology, 60-965 Poznan, Poland
Department of Robotics and Mechatronics, Faculty of Mechanical Engineering, Bialystok University of Technology, Wiejska St. 45C, 15-351 Bialystok, Poland
Faculty of Mechanical Engineering, Bialystok University of Technology, Bialystok, Poland
Department of Computer-Aided Design Systems, Lviv Polytechnic National University, 5 Mytropolyta Andreya St., building 4, 79013 Lviv, Ukraine

Innovation and Inventions in Aerospace and UAV Applications

Abstract submission deadline
30 June 2025
Manuscript submission deadline
31 August 2025
Viewed by
4471

Topic Information

Dear Colleagues,

As the Editors of the Topic “Innovation and Inventions in Aerospace and UAV Applications”, we would like to invite you to submit a paper to this collection. Recently, we have been experiencing a tremendous growth in the development of unmanned aerial vehicles (UAVs) and aerospace issues. Each month brings new ideas related to aviation in its broadest sense, becoming an even stronger accelerator for research in this field. This Topic aims to contribute to the innovative development of manned and unmanned aviation in many areas. Special consideration will be given to high-quality papers that address significant and inventive advances in design, modelling and control, as well as novel approaches and applications.

Potential topics include, but are not limited to, the following:

  • innovative UAV design;
  • new design approaches in aerospace and UAV;
  • unconventional airframe configuration;
  • new applications for UASs;
  • additive manufacuring in aviation;
  • new materials in aviation;
  • lattice and light-weight structures;
  • hybrid propulsion systems;
  • efficiency of flying platform;
  • green propulsion in aviation;
  • collaboration between manned and unmanned aircrafts;
  • navigation in aviation;
  • new machine learning techniques for UAS/aviation autonomous control;
  • dynamics, control and simulation of flying platforms;
  • embedded systems design for UAVs;
  • new security systems for wireless communications.

Dr. Andrzej Łukaszewicz
Prof. Dr. Mohamed Thariq Hameed Sultan
Dr. Quang Ha
Dr. Wojciech Giernacki
Dr. Leszek Ambroziak
Dr. Wojciech Tarasiuk
Dr. Andriy Holovatyy
Topic Editors

Keywords

  • CAx systems in aviation
  • efficiency of flying platform
  • smart materials in aviation
  • lattice and light-weight structures
  • AM in aviation
  • green propulsion
  • manned and unmanned aircrafts collaboration
  • UAV navigation
  • machine learning for autonomous control
  • fly control and simulation
  • new application for UAVs
  • MEMS sensors design
  • embedded systems design
  • electronics design in aviation
  • algorithms and software flying control

Participating Journals

Journal Name Impact Factor CiteScore Launched Year First Decision (median) APC
Aerospace
aerospace
2.6 3.0 2014 22.3 Days CHF 2400 Submit
Drones
drones
4.8 6.1 2017 17.9 Days CHF 2600 Submit
Inventions
inventions
3.4 5.4 2016 17.4 Days CHF 1800 Submit
Materials
materials
3.4 5.2 2008 13.9 Days CHF 2600 Submit
Sensors
sensors
3.9 6.8 2001 17 Days CHF 2600 Submit
Polymers
polymers
5.0 6.6 2009 13.7 Days CHF 2700 Submit
Applied Sciences
applsci
2.7 4.5 2011 16.9 Days CHF 2400 Submit
Energies
energies
3.2 5.5 2008 16.1 Days CHF 2600 Submit

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Published Papers (5 papers)

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20 pages, 14188 KiB  
Article
Enhancing Coastal Risk Recognition: Assessing UAVs for Monitoring Accuracy and Implementation in a Digital Twin Framework
by Rui Yuan, Hezhenjia Zhang, Ruiyang Xu and Liyuan Zhang
Appl. Sci. 2024, 14(7), 2879; https://doi.org/10.3390/app14072879 - 29 Mar 2024
Viewed by 331
Abstract
This paper addresses the intricate challenges of coastal management, particularly in rapidly forming tidal flats, emphasizing the need for innovative monitoring strategies. The dynamic coastal topography, exemplified by a newly formed tidal flat in Shanghai, underscores the urgency of advancements in coastal risk [...] Read more.
This paper addresses the intricate challenges of coastal management, particularly in rapidly forming tidal flats, emphasizing the need for innovative monitoring strategies. The dynamic coastal topography, exemplified by a newly formed tidal flat in Shanghai, underscores the urgency of advancements in coastal risk recognition. By utilizing a digital twin framework integrated with state-of-the-art unmanned aerial vehicles (UAVs), we systematically evaluate three configurations and identify the optimal setup incorporating real-time kinematics (RTK) and light detection and ranging (LiDAR). This UAV configuration excels in efficiently mapping the 3D coastal terrain. It has an error of less than 0.1 m when mapping mudflats at an altitude of 100 m. The integration of UAV data with a precise numerical ocean model forms the foundation of our dynamic risk assessment framework. The results showcase the transformative potential of the digital twin framework, providing unparalleled accuracy and efficiency in coastal risk recognition. Visualization through Unity Engine or Unreal Engine enhances accessibility, fostering community engagement and awareness. By predicting and simulating potential risks in real-time, this study offers a forward-thinking strategy for mitigating coastal dangers. This research not only contributes a comprehensive strategy for coastal risk management but also sets a precedent for the integration of cutting-edge technologies in safeguarding coastal ecosystems. The findings are significant in paving the way for a more resilient and sustainable approach to coastal management, addressing the evolving environmental pressures on our coastlines. Full article
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34 pages, 2373 KiB  
Article
Modeling of the Flight Performance of a Plasma-Propelled Drone: Limitations and Prospects
by Sylvain Grosse, Eric Moreau and Nicolas Binder
Drones 2024, 8(3), 114; https://doi.org/10.3390/drones8030114 - 21 Mar 2024
Viewed by 652
Abstract
The resurgence in interest in aircraft electro-aerodynamic (EAD) propulsion has been sparked due to recent advancements in EAD thrusters, which generate thrust by employing a plasma generated through electrical discharge. With potentially quieter propulsion that could contribute to the generation of lift or [...] Read more.
The resurgence in interest in aircraft electro-aerodynamic (EAD) propulsion has been sparked due to recent advancements in EAD thrusters, which generate thrust by employing a plasma generated through electrical discharge. With potentially quieter propulsion that could contribute to the generation of lift or the control of attitude, it is important to determine the feasibility of an EAD-propelled airplane. First, the main propulsive characteristics (thrust generation and power consumption) of EAD thrusters were drawn from the literature and compared with existing technologies. Second, an algorithm was developed to couple standard equations of flight with EAD propulsion performance and treat the first-order interactions. It fairly replicated the performance of the only available autonomous EAD-propelled drone. A test case based on an existing commercial UAV of 10 kg equipped with current-generation EAD thrusters anticipated a flight of less than 10 min, lower than 30 m in height, and below 8 m · s −1 in velocity. Achieving over 2 h of flight at 30 m of height at 10 m · s −1 requires the current EAD thrust to be doubled without altering the power consumption. For the same flight performance as the baseline UAV, the prediction asked for a tenfold increase in the thrust at the same power consumption. Full article
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13 pages, 12174 KiB  
Article
Virtual Validation of In-Flight GNSS Signal Reception during Jamming for Aeronautics Applications
by Veenu Tripathi and Stefano Caizzone
Aerospace 2024, 11(3), 204; https://doi.org/10.3390/aerospace11030204 - 05 Mar 2024
Viewed by 966
Abstract
Accurate navigation is a crucial asset for safe aviation operation. The GNSS (Global Navigation Satellite System) is set to play an always more important role in aviation but needs to cope with the risk of interference, possibly causing signal disruption and loss of [...] Read more.
Accurate navigation is a crucial asset for safe aviation operation. The GNSS (Global Navigation Satellite System) is set to play an always more important role in aviation but needs to cope with the risk of interference, possibly causing signal disruption and loss of navigation capability. It is crucial, therefore, to evaluate the impact of interference events on the GNSS system on board an aircraft, in order to plan countermeasures. This is currently obtained through expensive and time-consuming flight measurement campaigns. This paper shows on the other hand, a method developed to create a virtual digital twin, capable of reconstructing the entire flight scenario (including flight dynamics, actual antenna, and impact of installation on aircraft) and predicting the signal and interference reception at airborne level, with clear benefits in terms of reproducibility and easiness. Through simulations that incorporate jamming scenarios or any other interference scenarios, the effectiveness of the aircraft’s satellite navigation capability in the real environment can be evaluated, providing valuable insights for informed decision-making and system enhancement. By extension, the method shown can provide the ability to predict real-life outcomes even without the need for actual flight, enabling the analysis of different antenna-aircraft configurations in a specific interference scenario. Full article
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14 pages, 2443 KiB  
Article
A Fruit Harvesting Mechanism Capable of Multidimensional Movements: A Preliminary Study on the Integrated Mechanism with a Hexacopter
by Hanmin Park, Hyeongseok Kang, Bohyun Hwang, Seonggun Joe and Byungkyu Kim
Aerospace 2024, 11(3), 203; https://doi.org/10.3390/aerospace11030203 - 04 Mar 2024
Viewed by 828
Abstract
This study introduces a fruit harvesting mechanism powered by a single motor, designed for integration with unmanned aerial vehicles (UAVs). The mechanism performs reciprocating motion by converting linear motion into rotational motion. Consequently, the end-effector can execute multi-dimensional kinematic trajectories, including biaxial and [...] Read more.
This study introduces a fruit harvesting mechanism powered by a single motor, designed for integration with unmanned aerial vehicles (UAVs). The mechanism performs reciprocating motion by converting linear motion into rotational motion. Consequently, the end-effector can execute multi-dimensional kinematic trajectories, including biaxial and rotational movements, synchronized with the motor’s position. These axial and rotational motions facilitate the gripper’s ability to reach, retrieve, and detach fruit from branches during the harvesting process. Notably, a critical consideration in designing this fruit harvesting mechanism is to generate the necessary torque at the end-effector while minimizing reaction forces and torque that could destabilize the UAV during flight. With these considerations in mind, this preliminary study aimed to harvest a Fuji apple and conduct a dynamic analysis. We constructed a prototype of the single motor-driven fruit harvesting mechanism using a suitable servo motor. To assess its mechanical performance and evaluate its impact on the hexacopter, we developed both a specific test platform featuring a six-spherical-prismatic-spherical parallel structure and a virtual environmental flight simulator. Overall, the results demonstrate the successful harvesting of a Fuji apple weighing approximately 300 g by the single motor-driven fruit harvesting mechanism, with no adverse effects observed on the hexacopter’s operation. Full article
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24 pages, 15722 KiB  
Article
Experimental Research into an Innovative Green Propellant Based on Paraffin–Stearic Acid and Coal for Hybrid Rocket Engines
by Grigore Cican, Alexandru Paraschiv, Adrian Nicolae Buturache, Andrei Iaroslav Hapenciuc, Alexandru Mitrache and Tiberius-Florian Frigioescu
Inventions 2024, 9(2), 26; https://doi.org/10.3390/inventions9020026 - 29 Feb 2024
Viewed by 846
Abstract
This study focuses on an innovative green propellant based on paraffin, stearic acid, and coal, used in hybrid rocket engines. Additionally, lab-scale firing tests were conducted using a hybrid rocket motor with gaseous oxygen as the oxidizer, utilizing paraffin-based fuels containing stearic acid [...] Read more.
This study focuses on an innovative green propellant based on paraffin, stearic acid, and coal, used in hybrid rocket engines. Additionally, lab-scale firing tests were conducted using a hybrid rocket motor with gaseous oxygen as the oxidizer, utilizing paraffin-based fuels containing stearic acid and coal. The mechanical performance results revealed that the addition of stearic acid and coal improved the mechanical properties of paraffin-based fuel, including tensile, compression, and flexural strength, under both ambient and sub-zero temperatures (−21 °C). Macrostructural and microstructural examinations, conducted through optical and scanning electron microscopy (SEM), highlighted its resilience, despite minimal imperfections such as impurities and micro-voids. These characteristics could be attributed to factors such as raw material composition and the manufacturing process. Following the mechanical tests, the second stage involved conducting a firing test on a hybrid rocket motor using the new propellant and gaseous oxygen. A numerical simulation was carried out using ProPEP software to identify the optimal oxidant-to-fuel ratio for the maximum specific impulse. Following simulations, it was observed that the specific impulse for the paraffin and for the new propellant differs very little at each oxidant-to-fuel (O/F) ratio. It is noticeable that the maximum specific impulse is achieved for both propellants around the O/F value of 2.2. It was observed that no hazardous substances were present, unlike in traditional solid propellants based on ammonium perchlorate or aluminum. Consequently, there are no traces of chlorine, ammonia, or aluminum-based compounds after combustion. The resulting components for the simulated motor include H2, H2O, O2, CO2, CO, and other combinations in insignificant percentages. It is worth noting that the CO concentration decreases with an increase in the O/F ratio for both propellants, and the differences between concentrations are negligible. Additionally, the CO2 concentration peaks at an O/F ratio of around 4.7. The test proceeded under normal conditions, without compromising the integrity of the test stand and the motor. These findings position the developed propellant as a promising candidate for applications in low-temperature hybrid rocket technology and pave the way for future advancements. Full article
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