Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
3.4
2.1
Journals
Aerospace
Special Issues
Aerodynamic Numerical Optimization in UAV Design
share announcement

Aerodynamic Numerical Optimization in UAV Design

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

Deadline for manuscript submissions: 30 November 2024 | Viewed by 3948

Special Issue Editor

Prof. Dr. Aleksandar M. Simonović

E-Mail Website
Guest Editor
Department of Aerospace Engineering, Faculty of Mechanical Engineering, University of Belgrade, Kraljice Marije 16, 11120 Belgrade 35, Serbia
Interests: modeling and simulation; aerodynamics; fluid mechanics; computational fluid dynamics; numerical simulation; numerical modeling; numerical analysis; CFD simulation; computational fluid mechanics; turbulence

Special Issue Information

Dear Colleagues,

Contemporary Unmanned Aerial Vehicles (UAVs) come with diverse aerodynamic configuration solutions, allowing their utilization in a wide range of challenging and demanding operational conditions.

Custom-tailored UAVs have evolved in various industries to meet predetermined mission profiles. Precision agriculture, construction and infrastructure, filmmaking and photography, environmental monitoring, logistics and delivery, mining and resource exploration, oil and gas, search and rescue, security and surveillance, and surveying and mapping are just some of the industries that have been substantially influenced by their development.

The progressive development of UAVs featuring remote or automated flight and mission controls has superseded manned aircraft, eliminating the need for onboard pilots in many critical roles.

While these technologies have seen significant progress in recent years and play a vital role in these domains, there is a growing need to optimize their aerodynamic characteristics in order to enhance their performance, stability, maneuverability, effectiveness, and efficiency.

Aerodynamic numerical optimization is essential in the design of UAVs. Optimized aerodynamics enable higher flight speeds, longer endurance, and increased payload capacity, resulting in improved operational efficiency and increased stability and maneuverability, allowing UAVs to perform complex missions and tasks with precision.

Moreover, optimized designs can reduce energy consumption and extend flight times with a positive environmental impact.

Therefore, exploring and investigating the field of aerodynamic numerical optimization is crucial to unlocking the full potential of UAVs across various sectors.

Furthermore, with notable advancements in Computational Fluid Dynamics (CFD) and optimization methods, traditional approaches to UAV design that rely heavily on experimental testing and analytical models can be circumvented in order to efficiently explore, investigate, and enhance the aerodynamic characteristics of UAVs.

This Special Issue focuses on the state-of-the-art advancements in and applications of aerodynamic numerical optimization techniques in UAV design to explore the progress, applications, and challenges in this field.

Prof. Dr. Aleksandar M. Simonović
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. 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

  • unmanned aerial vehicle (UAV)
  • aerodynamic design optimization
  • aerodynamic shape optimization
  • optimization design
  • multi-objective optimization (MDO)
  • airfoil
  • wing
  • propeller
  • computational fluid dynamics (CFD)
  • aerodynamic configuration

Benefits of Publishing in a Special Issue

  • Ease of navigation: Grouping papers by topic helps scholars navigate broad scope journals more efficiently.
  • Greater discoverability: Special Issues support the reach and impact of scientific research. Articles in Special Issues are more discoverable and cited more frequently.
  • Expansion of research network: Special Issues facilitate connections among authors, fostering scientific collaborations.
  • External promotion: Articles in Special Issues are often promoted through the journal's social media, increasing their visibility.
  • e-Book format: Special Issues with more than 10 articles can be published as dedicated e-books, ensuring wide and rapid dissemination.

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

Published Papers (4 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Research

19 pages, 9961 KiB  
Article
Propeller Effects and Elasticity in Aerodynamic Analysis of Small Propeller-Driven Aircraft and UAVs
by Mohsen Rostami
Aerospace 2024, 11(8), 664; https://doi.org/10.3390/aerospace11080664 - 13 Aug 2024
Viewed by 174
Abstract
The importance of propeller effects and power contribution to the aerodynamics of small aircraft and unmanned aerial vehicles (UAVs) is indispensable. The aerodynamic analysis of wings in flight varies from rigid wing analysis due to wing deflection caused by transferred aerodynamic loads. This [...] Read more.
The importance of propeller effects and power contribution to the aerodynamics of small aircraft and unmanned aerial vehicles (UAVs) is indispensable. The aerodynamic analysis of wings in flight varies from rigid wing analysis due to wing deflection caused by transferred aerodynamic loads. This paper investigates the intertwined influence of propeller effects and elasticity on the aerodynamics of small propeller-driven aircraft and UAVs. Through a detailed methodology, a twin-engine propeller-driven aircraft is analyzed as a case study, providing insights into the proposed approach. Two critical analyses are presented: an examination of propeller effects in rigid aircraft and the incorporation of elastic wing properties. The former establishes a foundational understanding of aerodynamic behavior, while the latter explores the impact of wing elasticity on performance. Validation is achieved through comparative analysis with wind tunnel test results from a similar rigid structure aircraft. Utilizing NASTRAN software V2010.1, aerodynamic analysis of the elastic aircraft is conducted, complemented by semi-empirical insights. The results highlight the importance of these factors across different angles of attack. Furthermore, deviations from the rigid aircraft configuration emphasize the considerable influence of static aeroelasticity analysis, notably increasing longitudinal characteristics by approximately 20%, while showing a lower impact of 5% in lateral-directional characteristics. This study contributes to enhanced design and operational considerations for small propeller-driven aircraft, with implications for future research and innovation, particularly for the purpose of efficient concepts in advanced air mobility. Full article
(This article belongs to the Special Issue Aerodynamic Numerical Optimization in UAV Design)
►▼ Show Figures

Figure 1

16 pages, 5689 KiB  
Article
Flutter Optimization of Carbon/Epoxy Plates Based on a Fast Tree Algorithm
by Mirko Dinulović, Aleksandar Bengin, Branimir Krstić, Marjan Dodić and Miloš Vorkapić
Aerospace 2024, 11(8), 636; https://doi.org/10.3390/aerospace11080636 - 3 Aug 2024
Viewed by 383
Abstract
This study focuses on optimizing carbon/epoxy laminate configurations to maximize the flutter speed of composite structures using a Fast Tree Regression algorithm. Initially, a seed dataset was created, using finite element method (FEM) modal analysis for common stack-ups used in composite fins and [...] Read more.
This study focuses on optimizing carbon/epoxy laminate configurations to maximize the flutter speed of composite structures using a Fast Tree Regression algorithm. Initially, a seed dataset was created, using finite element method (FEM) modal analysis for common stack-ups used in composite fins and UAV components. The FEM analysis, based on the Lanczos algorithm for extracting modal frequencies in bending and torsion, was verified through experimental modal analysis using an AS-4/3501-6 composite system. Custom software was developed to interface with the FEA modal software, enabling the generation and augmentation of laminate dataset scenarios. The seed dataset was expanded until the coefficient of determination (R2) reached at least 0.95. Various regression algorithms, including Fast Forest Regression, Fast Tree Regression, Sdca Regression, and Lbfgs Poisson Regression, were evaluated. The Fast Tree Regression algorithm was selected for further analysis due to its superior performance. This algorithm was applied to a design space of nearly 2000 potential laminate candidates, focusing on symmetric lay-ups to avoid undesirable coupling between bending and torsion in UAV and missile control surfaces. The final optimized lay-ups, exhibit the highest Delta function values (the squared difference of modal frequencies in torsion and bending), indicating the expected highest flutter speeds. The results demonstrate the efficacy of tailored composite materials in achieving specific aerodynamic performance goals. Full article
(This article belongs to the Special Issue Aerodynamic Numerical Optimization in UAV Design)
►▼ Show Figures

Figure 1

20 pages, 11247 KiB  
Article
Lateral-Directional Aerodynamic Optimization of a Tandem Wing UAV Using CFD Analyses
by Ivan Kostić, Aleksandar Simonović, Olivera Kostić, Dušan Ivković and Dragoljub Tanović
Aerospace 2024, 11(3), 223; https://doi.org/10.3390/aerospace11030223 - 13 Mar 2024
Viewed by 1377
Abstract
This paper presents the second stage of a tandem fixed-wing unmanned aerial vehicle (UAV) aerodynamic development. In the initial stage, the UAV was optimized by analyzing its characteristics only in symmetrical flight conditions. Posted requirements were that both wings should produce relevant positive [...] Read more.
This paper presents the second stage of a tandem fixed-wing unmanned aerial vehicle (UAV) aerodynamic development. In the initial stage, the UAV was optimized by analyzing its characteristics only in symmetrical flight conditions. Posted requirements were that both wings should produce relevant positive lift, the initial stall must occur on the front wing first, the center of pressure should be close to the center of gravity, and longitudinal static stability should be in the optimum range. Computational fluid dynamic (CFD) analyses were performed, where the applied calculation model was derived from the authors’ previous successful projects. The eighth version TW V8 has satisfied all longitudinal requirements. Lateral-directional CFD analyses of V8 showed that the ratio of the lateral and directional stability at the nominal cruising regime was optimal, but both lateral and directional static stabilities were too high. On further development versions, the lower vertical tail was eliminated, a negative dihedral was implemented on the front wing, and four inverted blended winglets were added. Version TW V14 has largely improved lateral and directional stability characteristics, while their optimum ratio at the cruising regime was preserved. Longitudinal characteristics were also well preserved. Maximum lift coefficient and lift-to-drag ratio were increased, compared to the V8. Full article
(This article belongs to the Special Issue Aerodynamic Numerical Optimization in UAV Design)
►▼ Show Figures

Figure 1

17 pages, 4381 KiB  
Article
The Aerodynamic Performance of a Novel Overlapping Octocopter Considering Horizontal Wind
by Yao Lei, Jie Wang and Yazhou Li
Aerospace 2023, 10(10), 902; https://doi.org/10.3390/aerospace10100902 - 22 Oct 2023
Cited by 1 | Viewed by 1407
Abstract
This paper investigates the aerodynamic performance of an overlapping octocopter with the effect of horizontal wind ranging from 0 to 4 m/s using both low-speed wind tunnel tests and numerical simulations. The hovering efficiency and the potential control strategies of the octocopter under [...] Read more.
This paper investigates the aerodynamic performance of an overlapping octocopter with the effect of horizontal wind ranging from 0 to 4 m/s using both low-speed wind tunnel tests and numerical simulations. The hovering efficiency and the potential control strategies of the octocopter under the effect of horizontal wind are also validated using blade element momentum theory. The velocity distribution, rotor pressure and vortex of the downwash flow with the horizontal wind are presented using the Computational Fluid Dynamics (CFD) method. Finally, wind tunnel tests were performed to obtain the thrust and power consumption with the rotor speed ranging from 1500 to 2200 rpm for horizontal winds at 0 m/s, 2.5 m/s and 4 m/s. The results showed that horizontal wind decreased the flight efficiency of the planar octocopter and had little effect on the coaxial octocopter. It is also interesting to note that horizontal wind is beneficial for thrust increments at a higher rotor speed and power decrements at a lower rotor speed for the overlapping octocopter. Specifically, the horizontal wind of 2.5 m/s for a lower rpm is presented with a power decrement with proper aerodynamic interference between the rotor blades. Additionally, the overlapping octocopter obtains a higher hover efficiency at 4 m/s compared to traditional octocopters, which is more suitable for flying in a cross wind with a more compact structure. Full article
(This article belongs to the Special Issue Aerodynamic Numerical Optimization in UAV Design)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-4
Back to TopTop