Honorary Special Issue for Prof. Max F. Platzer

A special issue of Drones (ISSN 2504-446X). This special issue belongs to the section "Drone Design and Development".

Deadline for manuscript submissions: 31 December 2024 | Viewed by 22087

Special Issue Editor


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Guest Editor
Department of Mechanical and Aerospace Engineering, New Mexico State University, Las Cruces, NM 88003, USA
Interests: energy harvesting; nonlinear dynamics; vibration and control; smart materials; aeroelasticity; fluid-structure interactions; micro-/nanoelectromechanical systems (MEMS/NEMS); flight dynamics
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Special Issue Information

Dear Colleagues,

Drones is pleased to publish a Special Issue in honor of Prof. Max F. Platzer, who is currently serving as adjunct professor of mechanical and aerospace engineering at the University of California Davis. Since 2006 he has served as the editor of the international review journal “Progress in Aerospace Sciences”.

Born in Vienna in 1933, Prof. Platzer studied mechanical engineering at the Technical University of Vienna from 1951 to 1957. He received a Diploma Engineer’s degree in 1957 and became an assistant professor of fluid mechanics and applied mathematics. In 1960, he accepted the position of special assistant to the chief of the Aerodynamics Branch at the NASA Marshall Space Flight Center and served as chief of the Theoretical Unsteady Aerodynamics Section from 1963 to 1966. His responsibilities were the development of improved aero-elastic analysis methods for flexible launch vehicles, such as Saturn V. In 1965, he received a Superior Achievement Award signed by Dr. Wernher von Braun for his contributions to the identification and analysis of a panel flutter problem on the Saturn V launch vehicle. Additionally, in 1964, he completed a dissertation under the guidance of Prof. Klaus Oswatitsch, chair professor of fluid mechanics at the Technical University of Vienna. The topic of the dissertation was the extension of Oswatitsch’s equivalence rule (known in the United States as Whitcomb’s area rule) to unsteady flows.

In 1966, he moved to the Lockheed-Georgia Research Center, where he served as chief of the Aeromechanics Section, with the responsibility for improving the aero-elastic analysis methods used for large flexible aircraft, such as the Galaxy-C5 aircraft. In 1970, he accepted an appointment as associate professor of aeronautics at the Naval Postgraduate School, where he was promoted to full professor in 1976 and served as department chair between 1978 and 1988 and 2000 and 2003. During his service at the Naval Postgraduate School, he worked on various aerodynamic, aero-elastic, flight mechanics, and propulsion problems related to naval aircraft. Among them was the computational and experimental investigation of flapping wing aerodynamics, leading to the demonstration of one of the very first flapping-wing micro-air vehicles in December 2002.

In 1992, he was elected Fellow of the American Society of Mechanical Engineers. In 1995, he received the distinguished professor medal of the Naval Postgraduate School. In 2000, he was elected Fellow of the American Institute of Aeronautics and Astronautics, and in 2021 he was elected honorary president of the International Sustainable Aviation and Energy Research Society.

Prof. Platzer is inventor/co-inventor of three U.S. patents and author/co-author of 256 publications. He is also editor/co-editor of 7 conference proceedings and books, including the AGARD Manual on Aeroelasticity in Axial-Flow Turbomachines, Vol. I, Unsteady Aerodynamics, March 1987, and Vol. II, Structural Dynamics and Aeroelasticity, June 1988, as well as “Standard Handbook for Aerospace Engineers, 2nd edition, published by McGrawHill, 2018. He is author/co-author of the following books:

  1. Cebeci, M. Platzer, H. Chen, K.C. Chang, J.P. Shao, “Analysis of Low-Speed Unsteady Airfoil Flows”, Springer 2004;
  2. M.F. Platzer and N. Sarigul-Klijn, “Aerohydronautical Power Engineering - Is it the Key to Abundant Renewable Energy and Potable Water ?” University Readers, San Diego, California, 2012;
  3. M.F. Platzer and N. Sargul-Klijn, “The Green Energy Ship Concept: Renewable Energy from Wind over Water”, Springer Briefs in Applied Science and Technology 2021

In honor and recognition of Prof. Platzer’s life-long scientific and educational contributions to the field of drones and aeronautical engineering, this Special Issue of Drones welcomes the submission of original research manuscripts or reviews in the areas of the design and flight dynamics of drones. The deadline for the submission of manuscripts is December 31st, 2022. Manuscripts will be published online on an ongoing basis after due processing.

Dr. Abdessattar Abdelkefi
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 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

  • UAV/μUAV/MAV/NAV
  • fixed-wing/rotary-wing/flapping-wing drones
  • space/marine/aerial/underwater drones
  • flight dynamics and control
  • drone design and development
  • fluid–structure interaction/aeroelasticity/hydroelasticity
  • bioinspiration and biomimicry
  • drone development, stability, and manufacturing

Published Papers (6 papers)

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Research

28 pages, 10665 KiB  
Article
Material Extrusion Additive Manufacturing of the Composite UAV Used for Search-and-Rescue Missions
by Sebastian-Marian Zaharia, Ionut Stelian Pascariu, Lucia-Antoneta Chicos, George Razvan Buican, Mihai Alin Pop, Camil Lancea and Valentin Marian Stamate
Drones 2023, 7(10), 602; https://doi.org/10.3390/drones7100602 - 25 Sep 2023
Cited by 1 | Viewed by 2626
Abstract
The additive processes used in the manufacture of components for unmanned aerial vehicles (UAVs), from composite filaments, have an important advantage compared to classical technologies. This study focused on three-dimensional design, preliminary aerodynamic analysis, fabrication and assembly of thermoplastic extruded composite components, flight [...] Read more.
The additive processes used in the manufacture of components for unmanned aerial vehicles (UAVs), from composite filaments, have an important advantage compared to classical technologies. This study focused on three-dimensional design, preliminary aerodynamic analysis, fabrication and assembly of thermoplastic extruded composite components, flight testing and search-rescue performance of an UAV. The UAV model was designed to have the highest possible structural strength (the fuselage has a structure with stiffening frames and the wing is a tri-spar), but also taking into account the limitations of the thermoplastic extrusion process. From the preliminary aerodynamic analysis of the UAV model, it was found that the maximum lift coefficient of 1.2 and the maximum drag coefficient of 0.06 were obtained at the angle of attack of 12°. After conducting flight tests, it can be stated that the UAV model, with components manufactured by the thermoplastic extrusion process, presented high stability and maneuverability, a wide range of speeds and good aerodynamic characteristics. The lack of this type of aircraft, equipped with electric motors, a traffic management system, and a thermal module designed for search-and-rescue missions, within the additive manufacturing UAV market, validates the uniqueness of the innovation of the UAV model presented in the current paper. Full article
(This article belongs to the Special Issue Honorary Special Issue for Prof. Max F. Platzer)
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22 pages, 2235 KiB  
Article
Stability Derivatives of Various Lighter-than-Air Vehicles: A CFD-Based Comparative Study
by Anoop Sasidharan, Ratna Kishore Velamati, Sheeja Janardhanan, Venkata Ramana Murthy Oruganti and Akram Mohammad
Drones 2022, 6(7), 168; https://doi.org/10.3390/drones6070168 - 07 Jul 2022
Cited by 1 | Viewed by 2036
Abstract
An aerostat with a single tether is proposed for the application of wind measurements at low altitudes. In the current study, the aerodynamic model parameters (stability derivatives) of the aerostat are investigated based on a CFD-based approach. The static, as well as the [...] Read more.
An aerostat with a single tether is proposed for the application of wind measurements at low altitudes. In the current study, the aerodynamic model parameters (stability derivatives) of the aerostat are investigated based on a CFD-based approach. The static, as well as the dynamic stability derivatives of the aerostats are presented. The calculation of the dynamic stability derivatives involves the simulation of the oscillations of the aerostats in their axial direction (surge), the vertical direction (heave) and angular motions with respect to the lateral direction (pitch). A forced sinusoidal oscillation is used for the simulation of the aerostat, and one stable period of oscillation is taken for the derivatives’ extraction. Four different aerostats are considered for the current study with four different angles of attack. The Zhiyuan aerostat, HAA aerostat, NPL aerostat and GNVR aerostat are the aerostats considered for this study. The stability derivative results obtained for the four aerostats are analyzed and compared with respect to their geometrical features. From the static aerodynamic characteristics, the Zhiyuan aerostat shows better performance than the other aerostats in terms of the lift–drag ratio. The dynamic stability derivatives of the Zhiyuan aerostat suggest its application as the proposed low-altitude wind measurement system. Full article
(This article belongs to the Special Issue Honorary Special Issue for Prof. Max F. Platzer)
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10 pages, 432 KiB  
Article
Lyapunov Stability of a Planar Vertical Take-Off and Landing Aircraft Exerting a Force in the Environment
by Rogelio Lozano, Samantha Calderón and Iván González-Hernández
Drones 2022, 6(6), 144; https://doi.org/10.3390/drones6060144 - 11 Jun 2022
Cited by 1 | Viewed by 2127
Abstract
This work proposes a simplified control method to stabilize the model of a nonlinear Planar Vertical Take-Off and Landing (PVTOL) system when a constant force is applied in the horizontal axis. Since the stability analysis is based on a Lyapunov function, exponential stability [...] Read more.
This work proposes a simplified control method to stabilize the model of a nonlinear Planar Vertical Take-Off and Landing (PVTOL) system when a constant force is applied in the horizontal axis. Since the stability analysis is based on a Lyapunov function, exponential stability is guaranteed when the initial conditions fall inside a domain of attraction that is also specified. The performance of the suggested control algorithm is demonstrated using numerical simulations. Full article
(This article belongs to the Special Issue Honorary Special Issue for Prof. Max F. Platzer)
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19 pages, 12811 KiB  
Article
Wake Propagation and Characteristics of a Multi-Rotor Unmanned Vehicle in Forward Flight
by Glen Throneberry, Adam Takeshita, Christopher Michael Hocut, Fangjun Shu and Abdessattar Abdelkefi
Drones 2022, 6(5), 130; https://doi.org/10.3390/drones6050130 - 17 May 2022
Cited by 2 | Viewed by 2549
Abstract
In this study, experimental investigations are used to explore the wake propagation and characteristics of a multi-rotor unmanned air vehicle (UAV) in a forward flight mission. Qualitative smoke visualization is used first to gain a qualitative understanding of wake characteristics above and below [...] Read more.
In this study, experimental investigations are used to explore the wake propagation and characteristics of a multi-rotor unmanned air vehicle (UAV) in a forward flight mission. Qualitative smoke visualization is used first to gain a qualitative understanding of wake characteristics above and below the body of the multi-rotor UAV which is used as guidance for quantitative particle image velocimetry (PIV) experiments which better resolve the region in the vicinity of the multi-rotor UAV body. The experimental results over a wide range of advance ratios show that as the advance ratio increases, achieved by either lower rotor speeds or higher flight speeds, the distance by which the wake propagates below the UAV is reduced. While above the UAV, the flow returns to the freestream flow closer to the body as the advance ratio increases. Therefore, this study concludes that proximity effects are reduced as the advance ratio increases. Findings from this study can be used to inform in situ sensor placement so that sensor readings are minimally affected by the wake from the multi-rotor UAV. Velocity measurement corrections are provided for sensors mounted above the UAV which can be used to improve sensor data reliability in forward flight. These results can advance autonomous sensing and increase the utility of multi-rotor UAV observations while providing designers and users further guidance to avoid proximity effects. Full article
(This article belongs to the Special Issue Honorary Special Issue for Prof. Max F. Platzer)
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20 pages, 26407 KiB  
Article
A Robust and Accurate Landing Methodology for Drones on Moving Targets
by Assaf Keller and Boaz Ben-Moshe
Drones 2022, 6(4), 98; https://doi.org/10.3390/drones6040098 - 15 Apr 2022
Cited by 6 | Viewed by 7643
Abstract
This paper presents a framework for performing autonomous precise landing of unmanned aerial vehicles (UAVs) on dynamic targets. The main goal of this work is to design the methodology and the controlling algorithms that will allow multi-rotor drones to perform a robust and [...] Read more.
This paper presents a framework for performing autonomous precise landing of unmanned aerial vehicles (UAVs) on dynamic targets. The main goal of this work is to design the methodology and the controlling algorithms that will allow multi-rotor drones to perform a robust and efficient landing in dynamic conditions of changing wind, dynamic obstacles, and moving targets. Unlike existing GNSS-based vertical landing solutions, the suggested framework does not rely on global positioning and uses adaptive diagonal approaching angle visual landing. The framework was designed to work on existing camera-drone platforms, without any need for additional sensors, and it was implemented using DJI’s API on Android devices. The presented concept of visual sliding landing (VSL) was tested on a wide range of commercial drones, performing hundreds of precise and robust autonomous landings on dynamic targets, including boats, cars, RC-boats, and RC-rovers. Full article
(This article belongs to the Special Issue Honorary Special Issue for Prof. Max F. Platzer)
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16 pages, 12227 KiB  
Article
Improving UAV Mission Quality and Safety through Topographic Awareness
by Jamie Wubben, Christian Morales, Carlos T. Calafate, Enrique Hernández-Orallo, Juan-Carlos Cano and Pietro Manzoni
Drones 2022, 6(3), 74; https://doi.org/10.3390/drones6030074 - 11 Mar 2022
Cited by 1 | Viewed by 3493
Abstract
The field of Unmanned Aerial Vehicles (UAVs) has progressed greatly in the last years. UAVs are now used for many applications and are often flown automatically. One commonly implemented feature in an automatic flight is that of following a mission at a stable [...] Read more.
The field of Unmanned Aerial Vehicles (UAVs) has progressed greatly in the last years. UAVs are now used for many applications and are often flown automatically. One commonly implemented feature in an automatic flight is that of following a mission at a stable altitude. However, this altitude is almost always referenced from the take-off location and does not take terrain profile levels into account. This is a critical and dangerous issue because if the terrain level changes abruptly (e.g., mountain regions or buildings in a city), this can lead to crashes or an unintended (illegal) high altitude. Our aim for this work is to provide a solution such that a constant altitude above ground level is maintained. To this end, we make use of the readily available Digital Elevation Models (DEMs). These models, which contain the terrain elevation, help us in dynamically adjusting the VTOL UAV altitude so that it remains nearly constant in relation to the ground. Results have shown that with the use of our method, the altitude can be maintained sufficiently constant while introducing a limited increase in flight time and battery consumption that is proportional to the terrain’s irregularity. In a moderately changing terrain, the error could be reduced to just ±5 m. Full article
(This article belongs to the Special Issue Honorary Special Issue for Prof. Max F. Platzer)
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