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Drones
Special Issues
Dynamics Modeling and Conceptual Design of UAVs
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Dynamics Modeling and Conceptual Design of UAVs

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

Deadline for manuscript submissions: 20 March 2025 | Viewed by 6727

Special Issue Editors

Prof. Dr. Ni Li

E-Mail Website
Guest Editor
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Interests: aircraft task planning and swarm control; UAV
Dr. Ban Wang

E-Mail Website
Guest Editor
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Interests: aircraft flight dynamics and control; UAV
Prof. Dr. Shuhui Bu

E-Mail Website
Guest Editor
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Interests: computer vision and machine learning; UAV
Dr. Mostafa Hassanalian

E-Mail Website
Guest Editor
Department of Mechanical Engineering, New Mexico Tech, Weir Hall, Room 208, Socorro, NM 87801, USA
Interests: drones (UAV/MAV/NAV/PAV): fixed wings, flapping wings, tilt-rotor/wing drones, morphing drones, space and marine drones
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Unmanned aerial vehicles (UAVs) have become increasingly popular and important in various applications, such as search, rescue, and delivery services. As technology advances, UAVs are expected to have even more versatile applications. However, the development of UAVs heavily relies on their dynamics modeling and conceptual design, which are critical for ensuring their performance, reliability, and safety.

Dynamics modeling of UAVs involves mathematical and computational models that capture the physical behaviors and interactions of UAVs with their environments. It helps researchers and engineers better understand the dynamics of UAVs and design control systems that can stabilize and control the UAVs in different mission scenarios. Meanwhile, conceptual design is the early stage of UAV design, where the UAVs' overall configuration, shape, and size are determined based on mission requirements and technical constraints. It directly affects the performance and capabilities of UAVs.

Given the crucial importance of dynamics modeling and conceptual design for UAVs, this Special Issue explores recent advances and challenges in this research area. The aim is to provide a platform for researchers and experts to share their latest findings, exchange ideas and insights, and enhance collaborations.

This Special Issue aims to collect papers (original research articles and review papers) to give insights into new developments in dynamic modeling and conceptual design of advanced UAVs. Potential topics include but are not limited to aerodynamic modeling of UAVs, system identification and parameter estimation of UAVs, development of control strategies for UAV stabilization and control, multi-disciplinary design optimization of UAVs, and design and analysis of novel UAV concepts and configurations.

The contributions to this Special Issue cover a wide range of topics related to UAV dynamics modeling and conceptual design, including but not limited to:

  • Aerodynamic modeling of UAVs;
  • System identification and parameter estimation of UAVs;
  • Development of control strategies for UAV stabilization and control;
  • Multi-disciplinary design optimization of UAVs;
  • Design and analysis of novel UAV concepts and configurations.

We believe this Special Issue will serve as a valuable reference and source of inspiration for researchers and practitioners involved in UAV dynamics modeling and conceptual design. We look forward to receiving your original research articles and reviews.

Prof. Dr. Ni Li
Dr. Ban Wang
Prof. Dr. Shuhui Bu
Dr. Mostafa Hassanalian
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

  • dynamics modeling
  • conceptual design
  • UAV
  • control strategies
  • system identification

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

Published Papers (6 papers)

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Research

24 pages, 1133 KiB  
Article
Dynamic Inversion-Enhanced U-Control of Quadrotor Trajectory Tracking
by Ahtisham Lone, Quanmin Zhu, Hamidreza Nemati and Paolo Mercorelli
Drones 2024, 8(10), 599; https://doi.org/10.3390/drones8100599 - 18 Oct 2024
Viewed by 544
Abstract
This study proposes a universal (U)-control enhanced with dynamic inversion for a class of multiple-input multiple-output (MIMO) quadrotor flight tracking operations. In the technique, a robust compensator is integrated with the U-controller to achieve stabilisation at the equilibrium and setpoint tracking in the [...] Read more.
This study proposes a universal (U)-control enhanced with dynamic inversion for a class of multiple-input multiple-output (MIMO) quadrotor flight tracking operations. In the technique, a robust compensator is integrated with the U-controller to achieve stabilisation at the equilibrium and setpoint tracking in the presence of any unmodelled uncertainties and external disturbances. A series of bench tests of simulated and real experiments on a Parrot Mambo quadrotor are conducted to show the design framework from the academic formulation to Simulink simulation and real flight tests. Full article
(This article belongs to the Special Issue Dynamics Modeling and Conceptual Design of UAVs)
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19 pages, 5990 KiB  
Article
Aerodynamic Interaction Minimization in Coaxial Multirotors via Optimized Control Allocation
by Andrea Berra, Miguel Ángel Trujillo Soto and Guillermo Heredia
Drones 2024, 8(9), 446; https://doi.org/10.3390/drones8090446 - 30 Aug 2024
Viewed by 908
Abstract
Coaxial multirotors, characterized by overlapping rotors, represent a common solution to increasing payload capacity while maintaining a compact platform size. However, the overlap between motors generates airflow disturbances that, if not taken into account properly, may decrease the system’s overall performance. In this [...] Read more.
Coaxial multirotors, characterized by overlapping rotors, represent a common solution to increasing payload capacity while maintaining a compact platform size. However, the overlap between motors generates airflow disturbances that, if not taken into account properly, may decrease the system’s overall performance. In this paper, aerodynamic interactions for coaxial multirotors are analyzed and characterized. Two rotor models are introduced, which account for the aerodynamic interaction between the upper and the lower rotor. Each model is accompanied by its corresponding mixer design and analyzed with respect to the state-of-the-art mixer solution for classical multirotor systems. The proposed approaches are tested through rotor stand experiments, simulations, and implementation on an actual coaxial platform. The results demonstrate the effectiveness of these models in mitigating the adverse aerodynamic effects, thereby improving the performance and efficiency of coaxial multirotor systems. Full article
(This article belongs to the Special Issue Dynamics Modeling and Conceptual Design of UAVs)
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22 pages, 814 KiB  
Article
Nonlinear Adaptive Control Design for Quadrotor UAV Transportation System
by Boyu Zhu and Dazhi Wang
Drones 2024, 8(9), 420; https://doi.org/10.3390/drones8090420 - 24 Aug 2024
Viewed by 554
Abstract
In response to the non-linear and underactuated characteristics of quadrotor UAV suspension transportation system, this paper proposes a novel control strategy aimed at achieving precise position control, attitude control, and anti-swing capabilities. Firstly, a dynamical model required for controller design is established through [...] Read more.
In response to the non-linear and underactuated characteristics of quadrotor UAV suspension transportation system, this paper proposes a novel control strategy aimed at achieving precise position control, attitude control, and anti-swing capabilities. Firstly, a dynamical model required for controller design is established through the Newton-Euler method. In the controller design process, the paper employs the energy method and barrier Lyapunov function to design a double-closed-loop nonlinear controller. This controller is capable of not only accurately controlling the position and attitude angles of the quadrotor UAV suspension transportation system but also effectively suppressing the swing of the payload. Building on this, considering the elastic deformation of the lifting cable, and by analyzing the forces in the Newton-Euler equations, this paper proposes an adaptive control design for the case where the length of the cable connecting the UAV and the payload is unknown. To validate the effectiveness of the proposed control scheme, comparative experiments were conducted in the MATLAB simulation environment, and the results indicate that the method proposed in this paper exhibits superior control performance compared to traditional controllers. Full article
(This article belongs to the Special Issue Dynamics Modeling and Conceptual Design of UAVs)
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25 pages, 11288 KiB  
Article
Novel Twist Morphing Aileron and Winglet Design for UAS Control and Performance
by Mir Hossein Negahban, Musavir Bashir, Clovis Priolet and Ruxandra Mihaela Botez
Drones 2024, 8(8), 392; https://doi.org/10.3390/drones8080392 - 13 Aug 2024
Viewed by 1188
Abstract
This study introduces a novel “twist morphing aileron and winglet” design for the Unmanned Aircraft System UAS-S45. Improving rolling efficiency through twist morphing ailerons and reducing induced drag through twist morphing winglets are the two main objectives of this study. A novel wing [...] Read more.
This study introduces a novel “twist morphing aileron and winglet” design for the Unmanned Aircraft System UAS-S45. Improving rolling efficiency through twist morphing ailerons and reducing induced drag through twist morphing winglets are the two main objectives of this study. A novel wing design is introduced, and a high-fidelity gradient-based aerodynamic shape optimization is performed for twist morphing ailerons and twist morphing winglets, separately, with specified objective functions. The twist morphing aileron is then compared to the conventional hinged aileron configuration in terms of rolling efficiency and other aerodynamic properties, in particular aircraft maneuverability. The results for twist morphing ailerons show that the novel morphing design increases the aileron efficiency by 34% compared to the conventional design and reduces induced drag by 61%. Next, twist morphing winglets are studied regarding the induced drag in cruise and climb flight conditions. The results for twist morphing winglets indicate that the novel design reduces induced drag by 25.7% in cruise flight and up to 16.51% in climb; it also decreases the total drag by up to 7.5% and increases aerodynamic efficiency by up to 9%. Full article
(This article belongs to the Special Issue Dynamics Modeling and Conceptual Design of UAVs)
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19 pages, 2614 KiB  
Article
Quadcopter Modeling Using a System for UAV Parameters Measurement
by Jozef Novotňák, Zoltán Szőke, Patrik Kašper and Miroslav Šmelko
Drones 2024, 8(7), 280; https://doi.org/10.3390/drones8070280 - 22 Jun 2024
Viewed by 1356
Abstract
This article deals with quadcopter modeling using a system for the measurement of unmanned aerial vehicle (UAV) parameters. UAVs are often equipped with various measurement devices and equipment for measurement, which significantly affects their weight. The currently available technical solutions and inventions do [...] Read more.
This article deals with quadcopter modeling using a system for the measurement of unmanned aerial vehicle (UAV) parameters. UAVs are often equipped with various measurement devices and equipment for measurement, which significantly affects their weight. The currently available technical solutions and inventions do not allow corrections to be made to the on-board control electronics settings without the need to perform a test flight, or without the need to create complex and time-consuming mathematical models of the unmanned aerial vehicle; therefore, it is desirable to create a new method for modeling the characteristics of an UAV based on static laboratory measurements. The goal of this paper is to create a dynamic model of a quadcopter that will be adapted to a system for measuring UAV parameters, specifically the thrust of individual motors, which will be the next step to creating a new method for modeling UAV characteristics. This method can be used in the future for tuning flight control algorithms, based on static laboratory measurements. Full article
(This article belongs to the Special Issue Dynamics Modeling and Conceptual Design of UAVs)
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18 pages, 6246 KiB  
Article
Ground Effect on the Thrust Performance of Staggered Rotor System
by He Zhu, Shaoxiong Wei, Hong Nie, Yuhao Du and Xiaohui Wei
Drones 2024, 8(4), 118; https://doi.org/10.3390/drones8040118 - 23 Mar 2024
Cited by 2 | Viewed by 1455
Abstract
In this study, the thrust performance of a staggered rotor system in-ground effect (IGE) and out-of-ground effect (OGE) while considering the interaction on wake characteristics were investigated experimentally. A thorough comprehension of their performance holds significant importance for trajectory planning, aircraft design, landing [...] Read more.
In this study, the thrust performance of a staggered rotor system in-ground effect (IGE) and out-of-ground effect (OGE) while considering the interaction on wake characteristics were investigated experimentally. A thorough comprehension of their performance holds significant importance for trajectory planning, aircraft design, landing safety, and energy-efficient landings. The complex interactions within staggered rotor systems and the impact of ground effects make rotor distance and ground interactions critical factors influencing near-ground flight performance. The study investigated the influence and enhancements of rotor thrust performance through an examination of rotor speed, lateral distance, and altitude. Experimental tests were conducted on two small-scale rotor models to assess the effects of these parameters. These experiments compared the performance of staggered rotor systems with isolated rotors, analyzing the competition mechanism between the thrust loss caused by interference and the thrust gain of rotors IGE. Furthermore, emphasis was placed on analyzing the thrust gain issues exhibited by staggered rotor systems under the condition of H = 2R. Additionally, the analysis was focused on identifying prominent relative positions for thrust performance and parameters for improving thrust performance in ground effects in staggered rotor systems. Full article
(This article belongs to the Special Issue Dynamics Modeling and Conceptual Design of UAVs)
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