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Drones, Volume 6, Issue 10 (October 2022) – 48 articles

Cover Story (view full-size image): We developed a new aerial tree branch sampler to examine the feasibility of detecting forest pathogens collected from upper canopy branches. The pathogen of interest in this study is Ceratocystis lukuohia, which has caused widespread mortality in native ‘ōhi‘a forests across Hawai‘i. We aerially sampled branches from ten symptomatic trees, producing 29 branch samples with a maximum diameter of 4.2 cm and length of >2 m. We successfully detected the target fungal pathogen from the collected branches and found that branch diameter, leaf presence and condition, and wood moisture content are important factors in pathogen detection in sampled branches. The Kūkūau branch sampler can retrieve branches 7 cm in diameter, furthering pathogenic research requiring larger samples for successful diagnostic testing. View this paper
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27 pages, 5604 KiB  
Article
Finite-Time Neuro-Sliding-Mode Controller Design for Quadrotor UAVs Carrying Suspended Payload
by Özhan Bingöl and Hacı Mehmet Güzey
Drones 2022, 6(10), 311; https://doi.org/10.3390/drones6100311 - 21 Oct 2022
Cited by 14 | Viewed by 3939
Abstract
Due to the quadrotor’s underactuated nature, suspended payload dynamics, parametric uncertainties, and external disturbances, designing a controller for tracking the desired trajectories for a quadrotor that carries a suspended payload is a challenging task. Furthermore, one of the most significant disadvantages of designing [...] Read more.
Due to the quadrotor’s underactuated nature, suspended payload dynamics, parametric uncertainties, and external disturbances, designing a controller for tracking the desired trajectories for a quadrotor that carries a suspended payload is a challenging task. Furthermore, one of the most significant disadvantages of designing a controller for nonlinear systems is the infinite-time convergence to the desired trajectory. In this paper, a finite-time neuro-sliding mode controller (FTNSMC) for a quadrotor with a suspended payload that is subject to parametric uncertainties and external disturbances is designed. By constructing a finite-time sliding mode controller, the quadrotor can follow the reference trajectories in finite time. Furthermore, despite time-varying nonlinear dynamics, parametric uncertainties, and external disturbances, a neural network structure is added to the controller to effectively reduce chattering phenomena caused by high switching gains, and significantly reduce the size of the control signals. Following the completion of the controller design, the system’s stability is demonstrated using the Lyapunov stability criterion. Extensive numerical simulations with various scenarios are run to demonstrate the effectiveness of the proposed controller. Full article
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<p>Quadrotor model with payload.</p>
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<p>Point mass payload model.</p>
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<p>Neural-network structure.</p>
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<p><italic>x</italic> positions of quadrotor for Scenario 1.</p>
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<p><italic>y</italic> positions of quadrotor for Scenario 1.</p>
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<p><italic>z</italic> positions of quadrotor for Scenario 1.</p>
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<p><inline-formula><mml:math id="mm178"><mml:semantics><mml:msub><mml:mi>u</mml:mi><mml:mn>1</mml:mn></mml:msub></mml:semantics></mml:math></inline-formula> control inputs for Scenario 1.</p>
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<p><inline-formula><mml:math id="mm179"><mml:semantics><mml:msub><mml:mi>s</mml:mi><mml:mn>1</mml:mn></mml:msub></mml:semantics></mml:math></inline-formula> sliding variables for Scenario 1.</p>
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<p><inline-formula><mml:math id="mm180"><mml:semantics><mml:msub><mml:mi>u</mml:mi><mml:mn>2</mml:mn></mml:msub></mml:semantics></mml:math></inline-formula> control inputs for Scenario 1.</p>
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<p><inline-formula><mml:math id="mm181"><mml:semantics><mml:msub><mml:mi>u</mml:mi><mml:mn>3</mml:mn></mml:msub></mml:semantics></mml:math></inline-formula> control inputs for Scenario 1.</p>
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<p><inline-formula><mml:math id="mm182"><mml:semantics><mml:msub><mml:mi>u</mml:mi><mml:mn>4</mml:mn></mml:msub></mml:semantics></mml:math></inline-formula> control inputs for Scenario 1.</p>
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<p>Quadrotor angles for proposed controller for Scenario 1.</p>
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<p>Trajectory of quadrotor in 3D space for Scenario 1.</p>
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<p>Change in neural-network weights for Scenario 1.</p>
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<p>Errors in <italic>x</italic>-axis for Scenario 2.</p>
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<p>Errors in <italic>y</italic>-axis for Scenario 2.</p>
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<p>Errors in <italic>z</italic>-axis for Scenario 2.</p>
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<p><inline-formula><mml:math id="mm183"><mml:semantics><mml:msub><mml:mi>u</mml:mi><mml:mn>1</mml:mn></mml:msub></mml:semantics></mml:math></inline-formula> control inputs for Scenario 2.</p>
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<p><inline-formula><mml:math id="mm184"><mml:semantics><mml:msub><mml:mi>u</mml:mi><mml:mn>2</mml:mn></mml:msub></mml:semantics></mml:math></inline-formula> control inputs for Scenario 2.</p>
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<p><inline-formula><mml:math id="mm185"><mml:semantics><mml:msub><mml:mi>u</mml:mi><mml:mn>3</mml:mn></mml:msub></mml:semantics></mml:math></inline-formula> control inputs for Scenario 2.</p>
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<p><inline-formula><mml:math id="mm186"><mml:semantics><mml:msub><mml:mi>u</mml:mi><mml:mn>4</mml:mn></mml:msub></mml:semantics></mml:math></inline-formula> control inputs for Scenario 2.</p>
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<p>Trajectory of quadrotor in 3D space for Scenario 2.</p>
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<p>Change in neural-network weights for Scenario 2.</p>
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28 pages, 1429 KiB  
Article
RISE: Rolling-Inspired Scheduling for Emergency Tasks by Heterogeneous UAVs
by Bowen Fei, Daqian Liu, Weidong Bao, Xiaomin Zhu and Mingyin Zou
Drones 2022, 6(10), 310; https://doi.org/10.3390/drones6100310 - 20 Oct 2022
Cited by 4 | Viewed by 1949
Abstract
The multiple unmanned aerial vehicles (UAVs) system is highly sought after in the fields of emergency rescue and intelligent transportation because of its strong perception and extensive coverage. Formulating a reasonable task scheduling scheme is essential to raising the task execution efficiency of [...] Read more.
The multiple unmanned aerial vehicles (UAVs) system is highly sought after in the fields of emergency rescue and intelligent transportation because of its strong perception and extensive coverage. Formulating a reasonable task scheduling scheme is essential to raising the task execution efficiency of the system. However, the dynamics of task arrival and the heterogeneity of UAV performance make it more difficult for multiple UAVs to complete the tasks. To address these issues, this paper focuses on the multi-UAV scheduling problem and proposes a method of rolling-inspired scheduling for emergency tasks by heterogeneous UAVs (RISE). In order to ensure that emergency tasks can be allocated to UAVs in a real-time manner, a task grouping strategy based on a density peaks (DP) clustering algorithm is designed, which can quickly select UAVs with matching performance for the tasks arriving at the system. Furthermore, an optimization model with multiple constraints is constructed, which takes the task profit and UAV flight cost as the objective function. Next, we devise a rolling-based optimization mechanism to ensure that the tasks with shorter deadlines are executed first while maximizing the objective function, so as to obtain the optimal task execution order for each UAV. We conduct several groups of simulation experiments, and extensive experimental results illustrate that the number of tasks successfully scheduled and the utilization rate of UAVs by RISE are superior to other comparison methods, and it also has the fastest running time. It further proves that RISE has the capability to improve the completion rate of emergency tasks and reduce the flight cost of multiple UAVs. Full article
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<p>The framework of RISE.</p>
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<p>Illustrations of task clustering phase: (<b>a</b>) task layout; (<b>b</b>) center selection; (<b>c</b>) task partition.</p>
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<p>Illustration of task clustering phase.</p>
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<p>Task location deployment in an outdoor environment.</p>
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<p>The flight routes generated by four methods: (<b>a</b>) SC; (<b>b</b>) FCM; (<b>c</b>) DPGA; (<b>d</b>) RISE.</p>
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<p>Comparison for the number of unscheduled tasks of the four methods: (<b>a</b>) <math display="inline"><semantics> <msub> <mi>U</mi> <mn>1</mn> </msub> </semantics></math>; (<b>b</b>) <math display="inline"><semantics> <msub> <mi>U</mi> <mn>2</mn> </msub> </semantics></math>; (<b>c</b>) <math display="inline"><semantics> <msub> <mi>U</mi> <mn>3</mn> </msub> </semantics></math>; (<b>d</b>) <math display="inline"><semantics> <msub> <mi>U</mi> <mn>4</mn> </msub> </semantics></math>; (<b>e</b>) <math display="inline"><semantics> <msub> <mi>U</mi> <mn>5</mn> </msub> </semantics></math>; (<b>f</b>) <math display="inline"><semantics> <msub> <mi>U</mi> <mn>6</mn> </msub> </semantics></math>.</p>
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<p>Average number of scheduled tasks by the four methods.</p>
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<p>The flight time of the UAV formation in each group of instances.</p>
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<p>The success rate of scheduled tasks.</p>
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22 pages, 3334 KiB  
Article
System Identification of Heterogeneous Multirotor Unmanned Aerial Vehicle
by Ayaz Ahmed Hoshu, Liuping Wang, Shahzeb Ansari, Abdul Sattar and Manzoor Hyder Alias Bilal
Drones 2022, 6(10), 309; https://doi.org/10.3390/drones6100309 - 20 Oct 2022
Cited by 4 | Viewed by 2437
Abstract
An energy efficient heterogeneous multirotor unmanned aerial system (UAS) is presented in this paper, wherein, the aerodynamical characteristics of both helicopter and quadrotor are obtained in a single multirotor design. It features the energy efficiency and endurance of a helicopter, while keeping the [...] Read more.
An energy efficient heterogeneous multirotor unmanned aerial system (UAS) is presented in this paper, wherein, the aerodynamical characteristics of both helicopter and quadrotor are obtained in a single multirotor design. It features the energy efficiency and endurance of a helicopter, while keeping the mechanical simplicity, control and maneuverability of a quadrotor; employing a single large central rotor to get majority of the lift and four small arm canted rotors for control. Developing the stable and robust control strategy requires the accurate model of system. Due to the added mechanical complexities of the new design including the existence of couplings and gyroscopics, the modelling through the dynamic equations of the multirotor would not be possible in providing accurate results. Therefore, precise system modelling is required for the development of stable and robust control strategy. This paper proposes a novel system identification method with the objective to experimentally estimation of the precise dynamic model of the heterogeneous multirotor. The approach comprises of the utilization of input excitation signals, frequency sampling filter and derivation of transfer functions through complex curve fitting method. To validate the accuracy of the obtained transfer functions, the experimentally auto-tuned PID controllers are implemented over the transfer functions. Custom designed fight controller is used to experimentally implement the proposed idea. Presented results demonstrate the efficacy of the proposed approach for heterogeneous multirotor UAS. Full article
(This article belongs to the Section Drone Design and Development)
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<p>Heterogeneous multirotor model.</p>
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<p>Hardware prototype of heterogeneous multirotor UAV.</p>
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<p>Test rig for roll and pitch axis.</p>
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<p>Test rig for roll and pitch axis.</p>
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<p>Roll rate response of heterogeneous multirotor under range of sinusoidal input signals. Solid lines: roll rate, dashed lines: input signal. (<b>a</b>) Input frequency: 0.5 Hz. (<b>b</b>) Input frequency: 1.0 Hz. (<b>c</b>) Input frequency: 2.2 Hz. (<b>d</b>) Input frequency: 3.1 Hz. (<b>e</b>) Input frequency: 4.5 Hz.</p>
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<p>Frequency response of the estimated transfer functions for roll axis with respect to experimental frequency points.</p>
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<p>Pitch rate response of heterogeneous multirotor under range of sinusoidal input signals. Solid lines: pitch rate, dashed lines: input signal. (<b>a</b>) Input frequency: 0.5 Hz. (<b>b</b>) Input frequency: 1.2 Hz. (<b>c</b>) Input frequency: 2.7 Hz. (<b>d</b>) Input frequency: 3.6 Hz. (<b>e</b>) Input frequency: 4.8 Hz.</p>
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<p>Frequency response of the estimated transfer functions for pitch axis with respect to frequency points.</p>
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<p>Yaw rate response of heterogeneous multirotor under range of sinusoidal input signals. Solid lines: yaw rate, dashed lines: input signal. (<b>a</b>) Input frequency: 0.2 Hz. (<b>b</b>) Input frequency: 0.4 Hz. (<b>c</b>) Input frequency: 0.7 Hz. (<b>d</b>) Input frequency: 1.2 Hz. (<b>e</b>) Input frequency: 1.5 Hz.</p>
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<p>Frequency response of the estimated transfer functions for pitch axis with respect to frequency points.</p>
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<p>Cascaded control system for attitude control.</p>
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<p>Roll angular response.</p>
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<p>Roll angular rate response.</p>
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<p>Pitch angular response.</p>
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<p>Pitch angular rate response.</p>
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<p>Yaw angular rate response.</p>
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19 pages, 13384 KiB  
Article
Small-Object Detection for UAV-Based Images Using a Distance Metric Method
by Helu Zhou, Aitong Ma, Yifeng Niu and Zhaowei Ma
Drones 2022, 6(10), 308; https://doi.org/10.3390/drones6100308 - 20 Oct 2022
Cited by 34 | Viewed by 9814
Abstract
Object detection is important in unmanned aerial vehicle (UAV) reconnaissance missions. However, since a UAV flies at a high altitude to gain a large reconnaissance view, the captured objects often have small pixel sizes and their categories have high uncertainty. Given the limited [...] Read more.
Object detection is important in unmanned aerial vehicle (UAV) reconnaissance missions. However, since a UAV flies at a high altitude to gain a large reconnaissance view, the captured objects often have small pixel sizes and their categories have high uncertainty. Given the limited computing capability on UAVs, large detectors based on convolutional neural networks (CNNs) have difficulty obtaining real-time detection performance. To address these problems, we designed a small-object detector for UAV-based images in this paper. We modified the backbone of YOLOv4 according to the characteristics of small-object detection. We improved the performance of small-object positioning by modifying the positioning loss function. Using the distance metric method, the proposed detector can classify trained and untrained objects through object features. Furthermore, we designed two data augmentation strategies to enhance the diversity of the training set. We evaluated our method on a collected small-object dataset; the proposed method obtained 61.00% mAP50 on trained objects and 41.00% mAP50 on untrained objects with 77 frames per second (FPS). Flight experiments confirmed the utility of our approach on small UAVs, with satisfying detection performance and real-time inference speed. Full article
(This article belongs to the Special Issue Advances in UAV Detection, Classification and Tracking)
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<p>Structure of the proposed small-object detection method, including data augmentation, backbone network and object positioning and object classification modules.</p>
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<p>Two data augmentation methods. The red line represents the background replacement and the yellow lines represent noise adding.</p>
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<p>Comparison of backbones. CSPDarknet53 is the backbone of YOLOv4. DCSPDarknet53 is a backbone for small objects. ADCSPDarknet53 is a backbone that increases the downsampling network layer.</p>
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<p>The structure of backbone network ADCSPDarknet53. Conv means convolution layer. BN denotes batch normalization. Activation layer uses ReLU function.</p>
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<p>Selection of positive sample. The yellow dots are anchor points. The red dots are positive samples expanded by YOLOv5. The blue dots are positive samples proposed in this article.</p>
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<p>The flowchart of object classification for fine and rough classification.</p>
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<p>(<b>a</b>,<b>b</b>) are example images in the collected small-object dataset. The images on the left show the pixel proportion of the object to be detected in the whole image, and the patches on the right are a zoomed-in version of the red box on the left images. (<b>c</b>) shows eight objects in the dataset. 1, 2 and 3 are three trained cars belonging to different sub-classes. 4, 5 and 6 are three trained planes belonging to different sub-classes. 7 is an untrained plane and 8 is an untrained car. 7 and 8 are objects that did not appear in the training set and validation set.</p>
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<p>Small-object detection experiment with other algorithms. (<b>a</b>) YOLOv4 algorithm detection results; (<b>b</b>) our algorithm detection results.</p>
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<p>Untrained object classification experiment with other algorithms. (<b>a</b>) YOLOv4 algorithm detection results; (<b>b</b>) our algorithm detection results. Different colors of bounding boxes mean different sub-classes, and the recognized untrained sub-class objects are labeled with ’new’.</p>
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<p>Training process of object positioning.</p>
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<p>Hardware system for flight experiments. (<b>a</b>) DJI Matrice M210v2 drone; (<b>b</b>) DJI camera; (<b>c</b>) Nvidia Jetson Xavier NX.</p>
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<p>(<b>a</b>) The first detection scenario is set to have the same objects as the collected dataset, but with different background. (<b>b</b>) The second detection scenario uses real vehicles as objects. The figure on the left shows part of the drone’s field of view, and the right images show different types of vehicles, with six labeled types and one unlabeled.</p>
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<p>(<b>a</b>) Detection results on small model objects with different backgrounds. (<b>b</b>) Detection results on seven types of vehicles.</p>
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22 pages, 5758 KiB  
Article
Multidisciplinary Analysis and Optimization Method for Conceptually Designing of Electric Flying-Wing Unmanned Aerial Vehicles
by Oscar Ulises Espinosa Barcenas, Jose Gabriel Quijada Pioquinto, Ekaterina Kurkina and Oleg Lukyanov
Drones 2022, 6(10), 307; https://doi.org/10.3390/drones6100307 - 19 Oct 2022
Cited by 5 | Viewed by 3708
Abstract
Current unmanned aerial vehicles have been designed by applying the traditional approach to aircraft conceptual design which has drawbacks in terms of the individual analysis of each discipline involved in the conception of new aircraft, the reliance on the designer’s experience and intuition, [...] Read more.
Current unmanned aerial vehicles have been designed by applying the traditional approach to aircraft conceptual design which has drawbacks in terms of the individual analysis of each discipline involved in the conception of new aircraft, the reliance on the designer’s experience and intuition, and the inability of evaluating all possible design solutions. Multidisciplinary analysis and optimization focus on solving these problems, by synthesizing all the disciplines involved and accounting for their mutual interaction. This study presents a multidisciplinary analysis and optimization method for conceptually designing electrical flying-wing micro-unmanned aerial vehicles. The conceptual design task was formulated as a non-linear mathematical programming problem. The method considers the trimming of the UAV during each mission profile phase, consisting of the climb, cruise, and descent. We used two algorithms, one for design space exploration and another for optimization. Typical examples of solving conceptual design problems were considered in the work: the modernization of an existing UAV; the effect of the change of the payload and endurance change on the takeoff weight; and the influence of different static margins on aerodynamic characteristics. The advantages of using this design method are the remotion of additional internal cycles to solve the sizing equation at each optimization step, and the possibility of not only obtaining a unique optimal solution but also a vector of optimal solutions. Full article
(This article belongs to the Section Drone Design and Development)
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Graphical abstract

Graphical abstract
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<p>Objective function and constraints calculation process.</p>
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<p>Forces acting on the UAV.</p>
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<p>Influence of the coefficient C on the airfoil shape.</p>
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<p>Determining the distance between the elevon aerodynamic center and center of gravity.</p>
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<p>Design space exploration process.</p>
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<p>Main optimization process.</p>
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<p>Geometrical verification of the UAV trimming.</p>
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<p>Response surface: (<b>a</b>) Take-off mass; (<b>b</b>) lift-to-drag ratio from aspect ratio and leading-edge sweep angle.</p>
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<p>Response surface: (<b>a</b>) Take-off mass; (<b>b</b>) lift-to-drag ratio from wing loading and cruise speed.</p>
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<p>Boomerang UAV appearance.</p>
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<p>Convergence graph of the maximum and minimum values of the objective function.</p>
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<p>UAV top view shape: (<b>a</b>) “Boomerang” UAV A; (<b>b</b>) UAV B; (<b>c</b>) UAV C.</p>
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<p>Weight summary of the UAV modernizing design task: (<b>a</b>) absolute weights in kg; (<b>b</b>) relative weights.</p>
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<p>Weight summary of the optimal vector of the MTOW dependence on the change of payload weight: (<b>a</b>) absolute weights in kg; (<b>b</b>) relative weights.</p>
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<p>Weight summary of the optimal vector of the MTOW dependence on the change of endurance: (<b>a</b>) absolute weights in kg; (<b>b</b>) relative weights.</p>
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<p>Aerodynamic characteristics dependence on the static margin: (<b>a</b>) angle of attack; (<b>b</b>) lift-to-drag ratio.</p>
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18 pages, 3975 KiB  
Article
UAV Detection Using Thrust Engine Electromagnetic Spectra
by Tomas Jačionis, Vytautas Urbanavičius, Andrius Katkevičius, Vytautas Abromavičius, Artūras Serackis, Tomyslav Sledevič and Darius Plonis
Drones 2022, 6(10), 306; https://doi.org/10.3390/drones6100306 - 19 Oct 2022
Cited by 1 | Viewed by 4543
Abstract
Artificial intelligence used in unmanned aerial vehicle (UAV) flight control systems tends to leave UAV control systems without any radio communication emissions, whose signatures in an electromagnetic spectrum (ES) are widely used to detect UAVs. There will be problems in the near future [...] Read more.
Artificial intelligence used in unmanned aerial vehicle (UAV) flight control systems tends to leave UAV control systems without any radio communication emissions, whose signatures in an electromagnetic spectrum (ES) are widely used to detect UAVs. There will be problems in the near future in detecting any dangerous threats associated with UAV swarms, kamikaze unmanned aerial vehicles (UAVs), or any other UAVs with electrically powered thrust engines because of the UAV’s flight capabilities in full radio silence mode. This article presents a different approach to the detection of electrically powered multi-rotor UAVs. The main idea is to register the electromagnetic spectrum of the electric thrust engines of the UAV, which varies because of the changing flight conditions. An experiment on a UAV’s electric thrust engine-produced electromagnetic spectrum is carried out, presenting the results of the flight-dependent characteristics, which were observed in the electromagnetic spectrum. The electromagnetic signature of the UAV’s electric thrust engines is analyzed, discussed, and compared with the most similar behaving electric engine, which was used on the ground as a domestic electric appliance. A precision tunable magnetic antenna is designed, manufactured, and tested in this article. The physical experiments have shown that the ES of the electric thrust engines of multi-rotor UAVs can be detected and recorded for recognition. The unique signatures of the ES of the multi rotor UAV electric engine are recorded and presented as a result of the carried-out experiments. A precision tunable magnetic antenna is evaluated for the reception of the UAV’s signature. Moreover, results were obtained during the performed experiments and discussions about the development of the future techniques for the identification of the ES fingerprints of the UAV’s electric thrust engine are carried out. Full article
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<p>The main UAV propulsion energy and engine types.</p>
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<p>Precision tunable variable inductance magnetic antenna. 1—antenna coil with cooper windings; 2—antenna coil holder; 3—linear motion actuated ferrite rod; 4—insulating textolite insert; 5—shaft of the precision linear actuator; 6—body of the precision linear actuator; 7—step motor of the linear actuator. The dimensions of the proposed and manufactured antenna are coil length—100 mm; coil diameter—13 mm; ferrite rod diameter—10 mm; ferrite rod length—200 mm; insulator length—50 mm; overall system length of the magnetic antenna—600 mm.</p>
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<p>The experimental test bench of the tripod interconnecting ball joint holder: 1—roll axis of the UAV fixture; 2—pitch axis of the UAV fixture; 3—yaw axis of the UAV fixture; 4—the UAV’s fixture connecting ball joint; 5—the UAV’s fixture horizontal stabilizer connecting rod; 6—the UAV’s fixture horizontal stabilizer counterweight; 7—UAV’s thrust engine; 8—holder.</p>
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<p>Performance of the physical experiments.</p>
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<p>Recorded signature of a 24 kHz electromagnetic spectrogram, generated by the thrust engines of the multi-rotor Eachine Tyro UAV.</p>
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<p>Spectrum of the multi-rotor Eachine Tyro UAV at the fifth operating mode while engines work at 50% of its maximum power.</p>
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<p>Spectrum of the multi-rotor Eachine Tyro UAV when the thrust motors are spinning at the minimal idle rotation speed.</p>
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<p>Recorded signature of a 92 kHz electromagnetic spectrogram, generated by the thrust engines of the multi-rotor DJI Mavic 2 Enterprise UAV.</p>
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<p>Recorded signature of a 40 kHz electromagnetic spectrogram, generated by the single BLDC motor of the Dewalt impact driver.</p>
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<p>Spectrogram of antenna with shifted frequency from 23 kHz to 46 kHz and back to 23 kHz, when 1—received UAV EM spectrum signature of the second harmonic; 2—stepless transition of magnetic antenna resonant frequency to the first harmonic of UAV EM spectrum signature; 3—received UAV EM spectrum signature of the first harmonic; 4—stepless transition of magnetic antenna resonant frequency to the second harmonic of UAV EM spectrum signature; 5—received UAV EM spectrum signature of the second harmonic.</p>
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<p>Spectrograms of engines with all visible harmonics and their widths in the 0–120 kHz frequency range: (<b>a</b>)—Eachine Tyro drone; (<b>b</b>)—DJI drone; (<b>c</b>)—Dewalt impact driver.</p>
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24 pages, 2356 KiB  
Article
Effect of Rotor Tilt on the Gust Rejection Properties of Multirotor Aircraft
by James F. Whidborne, Arthur P. Mendez and Alastair Cooke
Drones 2022, 6(10), 305; https://doi.org/10.3390/drones6100305 - 18 Oct 2022
Cited by 5 | Viewed by 2982
Abstract
In order to operate safely in windy and gusty conditions, multirotor VTOL aircraft require gust resilience. This paper shows that their gust rejection properties can be improved by applying a small amount of fixed outward rotor tilt. Standard aerodynamic models of the rotors [...] Read more.
In order to operate safely in windy and gusty conditions, multirotor VTOL aircraft require gust resilience. This paper shows that their gust rejection properties can be improved by applying a small amount of fixed outward rotor tilt. Standard aerodynamic models of the rotors are incorporated into two dynamic models to assess the gust rejection properties. The first case is a conceptual birotor planar VTOL aircraft. The dependence of the trim and stability on the tilt angle are analyzed. The aircraft is stabilized using a pole-placement approach in order to obtain consistent closed-loop station-keeping performance in still air. The effect of gusts on the resulting response is determined by simulation. The second case study is for a quadrotor with a 10° outward rotor tilt. The aerodynamic coefficients are analyzed for trimmed station-keeping over a range of steady wind speeds. An LQR controller is used to apply station-keeping that includes integral action, and the gust responses are again obtained using simulation. The results show that the outward rotor tilt causes the aircraft to pitch down into a lateral gust, providing lateral force that opposes the gust and so significantly improving the gust rejection properties. Full article
(This article belongs to the Section Drone Design and Development)
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Figure 1
<p>Components of the airflow incident on a rotor disc ([<a href="#B26-drones-06-00305" class="html-bibr">26</a>], p. 56).</p>
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<p>Depiction of the Draganflyer X-Pro quadrotor [<a href="#B23-drones-06-00305" class="html-bibr">23</a>].</p>
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<p>Thrust force mapping for constant airspeeds, <math display="inline"><semantics> <mrow> <mi>V</mi> <mo>∈</mo> <mo>{</mo> <mn>0</mn> <mo>,</mo> <mn>10</mn> <mo>,</mo> <mn>20</mn> <mo>}</mo> </mrow> </semantics></math> ms<sup>−1</sup>.</p>
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<p>Horizontal force mapping for constant airspeeds, <math display="inline"><semantics> <mrow> <mi>V</mi> <mo>∈</mo> <mo>{</mo> <mn>0</mn> <mo>,</mo> <mn>10</mn> <mo>,</mo> <mn>20</mn> <mo>}</mo> </mrow> </semantics></math> ms<sup>−1</sup>.</p>
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<p>Rotor torque mapping for constant airspeeds, <math display="inline"><semantics> <mrow> <mi>V</mi> <mo>∈</mo> <mo>{</mo> <mn>0</mn> <mo>,</mo> <mn>10</mn> <mo>,</mo> <mn>20</mn> <mo>}</mo> </mrow> </semantics></math> ms<sup>−1</sup>.</p>
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<p>Variation of thrust with airspeed for constant rotor speed, <math display="inline"><semantics> <mrow> <mo>Ω</mo> <mo>=</mo> <mn>150</mn> </mrow> </semantics></math> rad s<sup>−1</sup>.</p>
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<p>Schematic of the PVTOL vehicle including rotor tilt, <math display="inline"><semantics> <mi>Υ</mi> </semantics></math>.</p>
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<p>Pitch and rotor speed trim maps for the PVTOL with <math display="inline"><semantics> <mrow> <mi>Υ</mi> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Rotor speeds trim map for the PVTOL with <math display="inline"><semantics> <mrow> <mi>Υ</mi> <mo>=</mo> <mn>10</mn> <msup> <mrow/> <mo>°</mo> </msup> </mrow> </semantics></math>.</p>
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<p>Dependence of mean rotor speed trim on <math display="inline"><semantics> <mi>Υ</mi> </semantics></math> for the PVTOL at constant <math display="inline"><semantics> <mrow> <msub> <mi>V</mi> <mi>W</mi> </msub> <mo>=</mo> <mn>20</mn> </mrow> </semantics></math> ms<sup>−1</sup>.</p>
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<p>Variation of aerodynamic derivatives, <math display="inline"><semantics> <mrow> <mo>{</mo> <msub> <mi>Z</mi> <mi>w</mi> </msub> <mo>,</mo> <msub> <mi>X</mi> <mi>u</mi> </msub> <mo>,</mo> <msub> <mi>X</mi> <mi>q</mi> </msub> <mo>,</mo> <msub> <mi>M</mi> <mi>u</mi> </msub> <mo>,</mo> <msub> <mi>M</mi> <mi>q</mi> </msub> <mo>}</mo> </mrow> </semantics></math>, for the PVTOL with <math display="inline"><semantics> <mi>Υ</mi> </semantics></math> for <math display="inline"><semantics> <mrow> <msub> <mi>V</mi> <mi>W</mi> </msub> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Variation of real parts of eigenvalues of small perturbation model of the PVTOL for <math display="inline"><semantics> <mrow> <msub> <mi>V</mi> <mi>W</mi> </msub> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Variation of imaginary parts of eigenvalues of small perturbation model of the PVTOL for <math display="inline"><semantics> <mrow> <msub> <mi>V</mi> <mi>W</mi> </msub> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Variation of control derivatives <math display="inline"><semantics> <mrow> <mo>{</mo> <msub> <mi>M</mi> <mrow> <mi>u</mi> <mn>2</mn> </mrow> </msub> <mo>,</mo> <msub> <mi>X</mi> <mrow> <mi>u</mi> <mn>2</mn> </mrow> </msub> <mo>,</mo> <msub> <mi>Z</mi> <mrow> <mi>u</mi> <mn>1</mn> </mrow> </msub> <mo>}</mo> </mrow> </semantics></math> for the PVTOL with <math display="inline"><semantics> <mi>Υ</mi> </semantics></math> for <math display="inline"><semantics> <mrow> <msub> <mi>V</mi> <mi>W</mi> </msub> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Variation of disturbance derivatives <math display="inline"><semantics> <mrow> <mo>{</mo> <msub> <mi>M</mi> <msub> <mi>V</mi> <mi>W</mi> </msub> </msub> <mo>,</mo> <msub> <mi>X</mi> <msub> <mi>V</mi> <mi>W</mi> </msub> </msub> <mo>,</mo> <msub> <mi>Z</mi> <msub> <mi>V</mi> <mi>W</mi> </msub> </msub> <mo>}</mo> </mrow> </semantics></math> for the PVTOL with <math display="inline"><semantics> <mi>Υ</mi> </semantics></math> for <math display="inline"><semantics> <mrow> <msub> <mi>V</mi> <mi>W</mi> </msub> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Lateral position response of the PVTOL to a 10 m horizontal position step demand.</p>
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<p>Pitch angle response of the PVTOL to a 10 m horizontal position step demand.</p>
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<p>Vertical position response of the PVTOL to a 10 m horizontal position step demand.</p>
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<p>Rotor speed response of the PVTOL to a 10 m horizontal position step demand.</p>
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<p>Lateral position response of the PVTOL to a 5 ms<sup>−1</sup> horizontal wind speed step.</p>
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<p>Pitch angle response of the PVTOL to a 5 ms<sup>−1</sup> horizontal wind speed step.</p>
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<p>Vertical position response of the PVTOL to a 5 ms<sup>−1</sup> horizontal wind speed step.</p>
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<p>Rotor speed response of the PVTOL to a 5 ms<sup>−1</sup> horizontal wind speed step.</p>
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<p>Quadrotor vehicle schematic including outwards rotor tilt, <math display="inline"><semantics> <mi>Υ</mi> </semantics></math>.</p>
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<p>Variation of aerodynamic derivatives, <math display="inline"><semantics> <mrow> <mo>{</mo> <msub> <mi>X</mi> <mi>u</mi> </msub> <mo>,</mo> <msub> <mi>X</mi> <mi>w</mi> </msub> <mo>,</mo> <msub> <mi>Y</mi> <mi>v</mi> </msub> <mo>,</mo> <msub> <mi>Z</mi> <mi>u</mi> </msub> <mo>,</mo> <msub> <mi>Z</mi> <mi>w</mi> </msub> <mo>}</mo> </mrow> </semantics></math>, for the quadrotor with <math display="inline"><semantics> <msub> <mi>V</mi> <mi>W</mi> </msub> </semantics></math> for <math display="inline"><semantics> <mrow> <mi>Υ</mi> <mo>=</mo> <mn>10</mn> <msup> <mrow/> <mo>°</mo> </msup> </mrow> </semantics></math>.</p>
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<p>Variation of aerodynamic derivatives, <math display="inline"><semantics> <mrow> <mo>{</mo> <msub> <mi>X</mi> <mi>q</mi> </msub> <mo>,</mo> <msub> <mi>Y</mi> <mi>p</mi> </msub> <mo>,</mo> <msub> <mi>Y</mi> <mi>r</mi> </msub> <mo>,</mo> <msub> <mi>Z</mi> <mi>q</mi> </msub> <mo>}</mo> </mrow> </semantics></math>, for the quadrotor with <math display="inline"><semantics> <msub> <mi>V</mi> <mi>W</mi> </msub> </semantics></math> for <math display="inline"><semantics> <mrow> <mi>Υ</mi> <mo>=</mo> <mn>10</mn> <msup> <mrow/> <mo>°</mo> </msup> </mrow> </semantics></math>.</p>
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<p>Variation of aerodynamic derivatives, <math display="inline"><semantics> <mrow> <mo>{</mo> <msub> <mi>L</mi> <mi>p</mi> </msub> <mo>,</mo> <msub> <mi>M</mi> <mi>q</mi> </msub> <mo>,</mo> <msub> <mi>L</mi> <mi>r</mi> </msub> <mo>,</mo> <msub> <mi>N</mi> <mi>p</mi> </msub> <mo>,</mo> <msub> <mi>N</mi> <mi>r</mi> </msub> <mo>}</mo> </mrow> </semantics></math>, for the quadrotor with <math display="inline"><semantics> <msub> <mi>V</mi> <mi>W</mi> </msub> </semantics></math> for <math display="inline"><semantics> <mrow> <mi>Υ</mi> <mo>=</mo> <mn>10</mn> <msup> <mrow/> <mo>°</mo> </msup> </mrow> </semantics></math>.</p>
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<p>Variation of aerodynamic derivatives, <math display="inline"><semantics> <mrow> <mo>{</mo> <msub> <mi>X</mi> <mi>q</mi> </msub> <mo>,</mo> <msub> <mi>Y</mi> <mi>p</mi> </msub> <mo>,</mo> <msub> <mi>Y</mi> <mi>r</mi> </msub> <mo>,</mo> <msub> <mi>Z</mi> <mi>q</mi> </msub> <mo>}</mo> </mrow> </semantics></math>, for the quadrotor with <math display="inline"><semantics> <msub> <mi>V</mi> <mi>W</mi> </msub> </semantics></math> for <math display="inline"><semantics> <mrow> <mi>Υ</mi> <mo>=</mo> <mn>10</mn> <msup> <mrow/> <mo>°</mo> </msup> </mrow> </semantics></math>.</p>
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<p>Draganflyer X-Pro quadrotor LQR control schematic with integral action.</p>
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<p>Position response of the Draganflyer X-Pro quadrotor to a 10 m <span class="html-italic">x</span>-position step demand.</p>
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<p>Attitude response of the Draganflyer X-Pro quadrotor to a 10 m <span class="html-italic">x</span>-position step demand.</p>
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<p>Position response of the Draganflyer X-Pro quadrotor to a 10 ms<sup>−1</sup> wind gust step in <span class="html-italic">x</span>-direction.</p>
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<p>Attitude response of the Draganflyer X-Pro quadrotor to a 10 ms<sup>−1</sup> wind gust step in <span class="html-italic">x</span>-direction.</p>
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15 pages, 403 KiB  
Article
Joint Placement and Power Optimization of UAV-Relay in NOMA Enabled Maritime IoT System
by Woping Xu, Junhui Tian, Li Gu and Shaohua Tao
Drones 2022, 6(10), 304; https://doi.org/10.3390/drones6100304 - 18 Oct 2022
Cited by 6 | Viewed by 2872
Abstract
In this paper, an unmanned aerial vehicle is utilized as an aerial relay to connect onshore base station with offshore users in a maritime IoT system with uplink non-orthogonal multiple access enabled. A coordinated direct and relay transmission scheme is adopted in the [...] Read more.
In this paper, an unmanned aerial vehicle is utilized as an aerial relay to connect onshore base station with offshore users in a maritime IoT system with uplink non-orthogonal multiple access enabled. A coordinated direct and relay transmission scheme is adopted in the proposed system, where close shore maritime users directly communicate with onshore BS and offshore maritime users need assistance of an aerial relay to communicate with onshore BS. We aim to minimize the total transmit energy of the aerial relay by jointly optimizing the UAV hovering position and transmit power allocation. The minimum rate requirements of maritime users and transmitters’ power budgets are considered. The formulated optimization problem is non-convex due to its non-convex constraints. Therefore, we introduce successive convex optimization and block coordinate descent to decompose the original problem into two subproblems, which are alternately solved to optimize the UAV energy consumption with satisfying the proposed constraints. Numerical results indicate that the proposed algorithm outperformed the benchmark algorithm, and shed light on the potential of exploiting the energy-limited aerial relay in IoT systems. Full article
(This article belongs to the Special Issue UAV-Assisted Intelligent Vehicular Networks)
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Figure 1
<p>System model of maritime IoT system with a UAV relay.</p>
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<p>The flowchart of Algorithm 1.</p>
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<p>Horizontal locations of UAV with different NOMA total power pairs <math display="inline"><semantics> <msub> <mi>P</mi> <mi>t</mi> </msub> </semantics></math>.</p>
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<p>Power allocation of UAV to BS for each MRU with different NOMA total power pairs <math display="inline"><semantics> <msub> <mi>P</mi> <mi>t</mi> </msub> </semantics></math>.</p>
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<p>UAV transmit power with different NOMA pair total power <math display="inline"><semantics> <msub> <mi>P</mi> <mi>t</mi> </msub> </semantics></math>.</p>
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<p>UAV transmitted power with different MRU rate requirements <math display="inline"><semantics> <msub> <mover accent="true"> <mi>R</mi> <mo>¯</mo> </mover> <mi>k</mi> </msub> </semantics></math>.</p>
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12 pages, 3897 KiB  
Article
Parameter Optimization and Impacts on Oilseed Rape (Brassica napus) Seeds Aerial Seeding Based on Unmanned Agricultural Aerial System
by Songchao Zhang, Meng Huang, Chen Cai, Hua Sun, Xiaohui Cheng, Jian Fu, Qingsong Xing and Xinyu Xue
Drones 2022, 6(10), 303; https://doi.org/10.3390/drones6100303 - 17 Oct 2022
Cited by 1 | Viewed by 1946
Abstract
Aerial seeding based on the unmanned agricultural aerial system (UAAS) improves the seeding efficiency of oilseed rape (OSR) seeds, and solves the problem of OSR planting in mountainous areas where it is inconvenient to use ground seeding machines. Therefore, the UAAS has been [...] Read more.
Aerial seeding based on the unmanned agricultural aerial system (UAAS) improves the seeding efficiency of oilseed rape (OSR) seeds, and solves the problem of OSR planting in mountainous areas where it is inconvenient to use ground seeding machines. Therefore, the UAAS has been applied in aerial seeding to a certain degree in China. The effective broadcast seeding width (EBSW), broadcast seeding density (BSD) and broadcast seeding uniformity (BSU) are the important indexes that affect the aerial seeding efficiency and quality of OSR seeds. In order to investigate the effects of flight speed (FS) and flight height (FH) on EBSW, BSD and BSU, and to achieve the optimized parameter combinations of UAAS T30 on aerial seeding application, three levels of FS (4.0 m/s, 5.0 m/s and 6.0 m/s) and three levels of FH (2.0 m, 3.0 m and 4.0 m) experiments were carried out in the field with 6.0 kg seeds per ha. The results demonstrated that the EBSW was not constant as the FS and FH changed. In general, the EBSW showed a change trend of first increasing and then decreasing as the FH increased under the same FS, and showed a trend of decreasing as FS increased under the same FH. The EBSWs were over 3.0 m in the nine treatments, in which the maximum was 5.44 m (T1, 4.0 m/s, 2.0 m) while the minimum was 3.2 m (T9, 6.0 m/s, 4.0 m). The BSD showed a negative change correlation as the FS changed under the same FH, and the BSD decreased as the FH increased under 4.0 m/s FS, while it first increased and then decreased under the FS of 5.0 m/s and 6.0 m/s. The maximum BSD value was 140.12 seeds/m2 (T1, 4.0 m/s, 2.0 m), while the minimum was 40.17 seeds/m2 (T9, 6.0 m/s, 4.0 m). There was no obvious change in the trend of the BSU evaluated by the coefficients of variation (CV): the minimum CV was 13.01% (T6, 6.0 m/s, 3.0 m) and the maximum was 64.48% (T3, 6.0 m/s, 2.0 m). The statistical analyses showed that the FH had significant impacts on the EBSWs (0.01 < p-value < 0.05), the FS and the interaction between FH and FS both had extremely significant impacts on EBSWs (p-value < 0.01). The FH had extremely significant impacts on BSD (p-value < 0.01), the FS had no impacts on BSD (p-value > 0.05), and the interaction between FH and FS had significant impacts on BSD (0.01 < p-value < 0.05). There were no significant differences in the broadcast sowing uniformity (BSU) among the treatments. Taking the EBSW, BSD and BSU into consideration, the parameter combination of T5 (T9, 5.0 m/s, 3.0 m) was selected for aerial seeding. The OSR seed germination rate was over 36 plants/m2 (33 days) on average, which satisfied the requirements of OSR planting agronomy. This study provided some technical support for UAAS application in aerial seeding. Full article
(This article belongs to the Special Issue Feature Papers for Drones in Agriculture and Forestry Section)
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<p>UAAS T30 flying in the test field.</p>
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<p>Field experimental sampling layout (top view).</p>
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<p>OSR seeds collected on the glued board.</p>
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<p>EBSW changes under different heights. Note: EBSW4.0, EBSW5.0 and EBSW6.0 represent the EBSW when the FSs were 4.0 m/s, 5.0 m/s and 6.0 m/s, respectively.</p>
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<p>EBSW changes under different speeds. Note: EBSW2.0, EBSW3.0 and EBSW4.0 represent the ESW when the FHs were 2.0 m, 3.0 m and 4.0m, respectively.</p>
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<p>BSD changes under different heights. Note: BSD4.0, BSD5.0 and BSD6.0 represent the BSD when the FHs were 4.0 m/s, 5.0 m/s and 6.0 m/s, respectively.</p>
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<p>BSD changes under different speeds. Note: BSD2.0, BSD3.0 and BSD4.0 represent the BSD when the FSs were 2.0 m, 3.0 m and 4.0m, respectively.</p>
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<p>Broadcast seeding uniformity of each treatment by CVs.</p>
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<p>OSR plants in the field 33 days after aerial seeding experiment.</p>
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25 pages, 8647 KiB  
Article
Automatic Tuning and Turbulence Mitigation for Fixed-Wing UAV with Segmented Control Surfaces
by Abdul Sattar, Liuping Wang, Ayaz Ahmed Hoshu, Shahzeb Ansari, Haider-e Karar and Abdulghani Mohamed
Drones 2022, 6(10), 302; https://doi.org/10.3390/drones6100302 - 16 Oct 2022
Cited by 4 | Viewed by 3240
Abstract
Unlike bigger aircraft, the small fixed-wing unmanned aerial vehicles face significant stability challenges in a turbulent environment. To improve the flight performance, a fixed-wing UAV with segmented aileron control surfaces has been designed and deployed. A total of four ailerons are attached to [...] Read more.
Unlike bigger aircraft, the small fixed-wing unmanned aerial vehicles face significant stability challenges in a turbulent environment. To improve the flight performance, a fixed-wing UAV with segmented aileron control surfaces has been designed and deployed. A total of four ailerons are attached to the main wing and grouped into inner and outer aileron pairs. The controllers are automatically tuned by utilizing the frequency response data obtained via the frequency sampling filter and the relay with embedded integrator experiments. The hardware validation experiments are performed in the normal and turbulent flight environments under three configurations: inner aileron pair only, outer aileron pair only and collective actuation of all the aileron pairs. The error-threshold-based control is introduced to handle collective actuation of aileron pairs. The experiments have manifested that the collective usage of all aileron segments improves the roll attitude stability by a margin of 38.69% to 43.51% when compared to the independent actuation of aileron pairs in a turbulent atmosphere. Full article
(This article belongs to the Section Drone Design and Development)
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Figure 1
<p>The UAV model with dimensions.</p>
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<p>UAV mounted on roll rig inside Industrial wind tunnel (IWT). (<b>a</b>) Top view showing flight controller board and sensors ➀ along with battery ➁. (<b>b</b>) Bottom view showing inner segments ➃,➄ and outer segments ➂,➅.</p>
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<p>Flight controller with all I/O ports.</p>
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<p>Setup of relay with integrator.</p>
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<p>Location of fundamental frequency <math display="inline"><semantics> <mrow> <mo>(</mo> <msub> <mi>ω</mi> <mn>1</mn> </msub> <mo>)</mo> </mrow> </semantics></math> when using relay with integrator.</p>
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<p>Inner loop system identification for roll rate: Relay with embedded integrator experimental results for (<b>a</b>) Inner segments (<b>b</b>) Outer segments. Key: Dashed line shows relay excitation signal and solid line shows roll rate output.</p>
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<p>Inner loop system identification for roll rate: Two frequency points extracted from relay output data for (<b>a</b>) Inner segments (<b>b</b>) Outer segments. Key: Stars indicate the 3rd and the circles indicate the 7th frequency response points.</p>
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<p>Structure of inner loop with PID controller for roll rate control.</p>
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<p>Relay test setup for outer loop identification.</p>
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<p>Outer loop identification for roll angle: Relay with embedded integrator experimental results for (<b>a</b>) Inner segments (<b>b</b>) Outer segments. Key: Dashed line indicates relay excitation signal and solid line indicates roll rate output.</p>
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<p>Outer loop identification for roll angle: Two frequency points extracted from relay output data for (<b>a</b>) Inner segments (<b>b</b>) Outer segments. Key: Stars show the 3rd and circles show the 7th frequency response points.</p>
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<p>Cascade structure of inner and outer loops for roll angle control.</p>
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<p>Wind tunnel setup for turbulence generation. (<b>a</b>) UAV facing incoming tubulent flow. (<b>b</b>) Closer look at turbulence generating box.</p>
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<p>Sequence of experiments performed in the Wind Tunnel for Autotuned PID Controllers.</p>
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<p>Inner segments during laminar flow. (<b>a</b>) Roll angle; (<b>b</b>) Roll rate output. Key: Dashed line indicates reference signal and solid line indicates output data.</p>
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<p>Inner segments control (<math display="inline"><semantics> <msub> <mi>δ</mi> <mrow> <mi>a</mi> <mi>i</mi> </mrow> </msub> </semantics></math>) input (<b>a</b>) during laminar airflow (<b>b</b>); during turbulent air flow.</p>
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<p>Inner segments during turbulent flow. (<b>a</b>) Roll angle; (<b>b</b>) Roll rate output. Key: Dashed line indicates reference signal and solid line indicates output data.</p>
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<p>Outer segments during laminar flow. (<b>a</b>) Roll angle; (<b>b</b>) Roll rate output. Key: Dashed line indicates reference signal and solid line indicates output data.</p>
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<p>Outer segments control (<math display="inline"><semantics> <msub> <mi>δ</mi> <mrow> <mi>a</mi> <mi>o</mi> </mrow> </msub> </semantics></math>) input (<b>a</b>) During laminar airflow (<b>b</b>) During turbulent air flow.</p>
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<p>Outer segments during turbulent flow. (<b>a</b>) Roll angle; (<b>b</b>) Roll rate output. Key: Dashed line indicates reference signal and solid line indicates output data.</p>
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<p>Cascade structure using error-threshold based control of the inner and outer segments.</p>
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<p>The error-threshold based control in laminar flow. (<b>a</b>) Roll angle and (<b>b</b>) roll rate output. Key: Dashed line indicates reference signal and solid line indicates output data.</p>
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<p>The error-threshold based control in laminar flow. (<b>a</b>) Control signal for the outer segment servos (<math display="inline"><semantics> <msub> <mi>δ</mi> <mrow> <mi>a</mi> <mi>o</mi> </mrow> </msub> </semantics></math>). (<b>b</b>) Control signal for the inner segments (<math display="inline"><semantics> <msub> <mi>δ</mi> <mrow> <mi>a</mi> <mi>i</mi> </mrow> </msub> </semantics></math>). (<b>c</b>) Angle error magnitude.</p>
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<p>The error-threshold-based control in turbulent flow. (<b>a</b>) Roll angle (<b>b</b>) roll rate output. Key: Dashed line indicates reference signal and solid line indicates output data.</p>
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<p>The error-threshold-based control in turbulent flow (<b>a</b>) Control signal for outer segment servos (<math display="inline"><semantics> <msub> <mi>δ</mi> <mrow> <mi>a</mi> <mi>o</mi> </mrow> </msub> </semantics></math>); (<b>b</b>) Control signal for the inner segments (<math display="inline"><semantics> <msub> <mi>δ</mi> <mrow> <mi>a</mi> <mi>i</mi> </mrow> </msub> </semantics></math>); (<b>c</b>) Angle error magnitude.</p>
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21 pages, 2787 KiB  
Article
Monitoring and Cordoning Wildfires with an Autonomous Swarm of Unmanned Aerial Vehicles
by Fabrice Saffre, Hanno Hildmann, Hannu Karvonen and Timo Lind
Drones 2022, 6(10), 301; https://doi.org/10.3390/drones6100301 - 14 Oct 2022
Cited by 33 | Viewed by 5582
Abstract
Unmanned aerial vehicles, or drones, are already an integral part of the equipment used by firefighters to monitor wildfires. They are, however, still typically used only as remotely operated, mobile sensing platforms under direct real-time control of a human pilot. Meanwhile, a substantial [...] Read more.
Unmanned aerial vehicles, or drones, are already an integral part of the equipment used by firefighters to monitor wildfires. They are, however, still typically used only as remotely operated, mobile sensing platforms under direct real-time control of a human pilot. Meanwhile, a substantial body of literature exists that emphasises the potential of autonomous drone swarms in various situational awareness missions, including in the context of environmental protection. In this paper, we present the results of a systematic investigation by means of numerical methods i.e., Monte Carlo simulation. We report our insights into the influence of key parameters such as fire propagation dynamics, surface area under observation and swarm size over the performance of an autonomous drone force operating without human supervision. We limit the use of drones to perform passive sensing operations with the goal to provide real-time situational awareness to the fire fighters on the ground. Therefore, the objective is defined as being able to locate, and then establish a continuous perimeter (cordon) around, a simulated fire event to provide live data feeds such as e.g., video or infra-red. Special emphasis was put on exclusively using simple, robust and realistically implementable distributed decision functions capable of supporting the self-organisation of the swarm in the pursuit of the collective goal. Our results confirm the presence of strong nonlinear effects in the interaction between the aforementioned parameters, which can be closely approximated using an empirical law. These findings could inform the mobilisation of adequate resources on a case-by-case basis, depending on known mission characteristics and acceptable odds (chances of success). Full article
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<p>Survival curves indicating how long a fire is statistically expected to burn, for three different <math display="inline"><semantics> <msub> <mi mathvariant="italic">fuel</mi> <mn>0</mn> </msub> </semantics></math>, the initial amount of fuel.</p>
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<p>Illustration of weighting factors. No wind, symmetrical propagation (<b>A</b>). North-westerly wind favouring propagation towards the southeast (<b>B</b>).</p>
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<p>Calculation of the resultant vector. All detected heat sources are added up, taking into account range and fire intensity (<b>A</b>). The nearby source outside the cone of vision (west-northwest) is not included. The resultant vector points into the average direction (<b>B</b>).</p>
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<p>The three drone behaviours and the triggers that cause a behaviour switch.</p>
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<p>The changes in behaviour when locating a fire (by the device itself, <b>A</b> or by a neighbouring drone, <b>B</b>). Once a device is in <tt>tracking</tt> mode, it can only change into <tt>evading</tt> mode if its ambient temperatures get too hot. Once an acceptable safety distance has been reached, a drone will automatically revert to the <tt>tracking</tt> behaviour until the mission is completed.</p>
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<p>Example of a successfully established perimeter. The arrows point to the two nearest neighbours of every UAV. For a symmetrical cordon to be created, all the connections between its members must be bidirectional. This is the case here for the set containing drones 8,3,5,4,1,7,6 (2, whose nearest neighbours are 3 and 4 but is not one of theirs, is not included).</p>
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<p>Typical outcome of a simulation run in the symmetrical (<b>A</b>) and biased propagation (<b>B</b>) scenarios (the white dot marks the point of origin). The furthest reach of the fire, the time it took for it to reach the edge of the arena and the total area destroyed up to that time are recorded. The elevation curves indicate progression and are 2′ apart.</p>
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<p>Simulation results (1000 independent realisations per combination of parameter values). (<b>A</b>): comparison between symmetrical and biased fire propagation. (<b>B</b>): <span class="html-italic">“survival”</span> curve representation of the size (surface area) of the blaze when it was successfully encircled, in the biased propagation case.</p>
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<p>Performance evaluation for variable arena and swarm sizes. Every data point is the fraction of simulation runs that resulted in a successful perimeter being established, out of 1000 independent realisations (symmetrical fire propagation scenario).</p>
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<p>The Frequency distribution of successful encirclements as a function of the interval between locating a fire and establishing a perimeter, for three different swarm sizes (<math display="inline"><semantics> <mrow> <mi>n</mi> <mo>=</mo> <mn>6</mn> </mrow> </semantics></math>, 8 and 10), operating in the largest arena (≈831 ha). Results are for the symmetrical fire propagation scenario.</p>
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22 pages, 1028 KiB  
Article
Robust Neural Network Consensus for Multiagent UASs Based on Weights’ Estimation Error
by Alejandro Morfin-Santana, Filiberto Muñoz, Sergio Salazar and José Manuel Valdovinos
Drones 2022, 6(10), 300; https://doi.org/10.3390/drones6100300 - 13 Oct 2022
Cited by 2 | Viewed by 2091
Abstract
We propose a neural network consensus strategy to solve the leader–follower problem for multiple-rotorcraft unmanned aircraft systems (UASs), where the goal of this work was to improve the learning based on a set of auxiliary variables and first-order filters to obtain the estimation [...] Read more.
We propose a neural network consensus strategy to solve the leader–follower problem for multiple-rotorcraft unmanned aircraft systems (UASs), where the goal of this work was to improve the learning based on a set of auxiliary variables and first-order filters to obtain the estimation error of the neural weights and to introduce this error information in the update laws. The stability proof was conducted based on Lyapunov’s theory, where we concluded that the formation errors and neural weights’ estimation error were uniformly ultimately bounded. A set of simulation results were conducted in the Gazebo environment to show the efficacy of the novel update laws for the altitude and translational dynamics of a group of UASs. The results showed the benefits and insights into the coordinated control for multiagent systems that considered the weights’ error information compared with the consensus strategy based on classical σ-modification. A comparative study with the performance index ITAE and ITSE showed that the tracking error was reduced by around 45%. Full article
(This article belongs to the Special Issue Multi-UAVs Control)
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<p>Structure of a quadrotor aerial vehicle with the body frame and inertial frame.</p>
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<p>Experiments for the dynamics in Gazebo. (<b>a</b>) Response and identification for the dynamics of <span class="html-italic">z</span> within the Gazebo environment. (<b>b</b>) Response and identification for the dynamics of <math display="inline"><semantics> <mi>θ</mi> </semantics></math> within the Gazebo environment.</p>
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<p>Experiments for attitude dynamics in Gazebo. (<b>a</b>) Response and identification for the dynamics of <math display="inline"><semantics> <mi>ϕ</mi> </semantics></math> within the Gazebo environment; (<b>b</b>) Response and identification for the dynamics of <math display="inline"><semantics> <mi>ψ</mi> </semantics></math> within the Gazebo environment.</p>
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<p>Communication graph proposed for the multiagent systems.</p>
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<p>Consensus with a traditional nominal distributed controller for 4 agents <math display="inline"><semantics> <msub> <mi>z</mi> <mi>n</mi> </msub> </semantics></math> tracking a virtual leader <math display="inline"><semantics> <msub> <mi>z</mi> <mn>0</mn> </msub> </semantics></math>.</p>
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<p>Consensus with adaptive term for 4 agents <math display="inline"><semantics> <msub> <mi>z</mi> <mi>n</mi> </msub> </semantics></math> tracking a virtual leader <math display="inline"><semantics> <msub> <mi>z</mi> <mn>0</mn> </msub> </semantics></math>.</p>
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<p>Consensus with our algorithm proposed for 4 agents <math display="inline"><semantics> <msub> <mi>z</mi> <mi>n</mi> </msub> </semantics></math> tracking a virtual leader <math display="inline"><semantics> <msub> <mi>z</mi> <mn>0</mn> </msub> </semantics></math>.</p>
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<p>Time development of the positions of the follower agents tracking the circular path. (<b>a</b>) Consensus performance in the <span class="html-italic">X</span>-axis. (<b>b</b>) Consensus performance in the <span class="html-italic">Y</span>-axis.</p>
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<p>Consensus performance in horizontal plane <span class="html-italic">X</span>–<span class="html-italic">Y</span>.</p>
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21 pages, 6462 KiB  
Article
Effects of the Spatial Resolution of UAV Images on the Prediction and Transferability of Nitrogen Content Model for Winter Wheat
by Yan Guo, Jia He, Jingyi Huang, Yuhang Jing, Shaobo Xu, Laigang Wang, Shimin Li and Guoqing Zheng
Drones 2022, 6(10), 299; https://doi.org/10.3390/drones6100299 - 13 Oct 2022
Cited by 7 | Viewed by 2869
Abstract
UAV imaging provides an efficient and non-destructive tool for characterizing farm information, but the quality of the UAV model is often affected by the image’s spatial resolution. In this paper, the predictability of models established using UAV multispectral images with different spatial resolutions [...] Read more.
UAV imaging provides an efficient and non-destructive tool for characterizing farm information, but the quality of the UAV model is often affected by the image’s spatial resolution. In this paper, the predictability of models established using UAV multispectral images with different spatial resolutions for nitrogen content of winter wheat was evaluated during the critical growth stages of winter wheat over the period 2021–2022. Feature selection based on UAV image reflectance, vegetation indices, and texture was conducted using the competitive adaptive reweighted sampling, and the random forest machine learning method was used to construct the prediction model with the optimized features. Results showed that model performance increased with decreasing image spatial resolution with a R2, a RMSE, a MAE and a RPD of 0.84, 4.57 g m−2, 2.50 g m−2 and 2.34 (0.01 m spatial resolution image), 0.86, 4.15 g m−2, 2.82 g m−2 and 2.65 (0.02 m), and 0.92, 3.17 g m−2, 2.45 g m−2 and 2.86 (0.05 m), respectively. Further, the transferability of models differed when applied to images with coarser (upscaling) or finer (downscaling) resolutions. For upscaling, the model established with the 0.01 m images had a R2 of 0.84 and 0.89 when applied to images with 0.02 m and 0.05 m resolutions, respectively. For downscaling, the model established with the 0.05 m image features had a R2 of 0.86 and 0.83 when applied to images of 0.01 m and 0.02 m resolutions. Though the image spatial resolution affects image texture features more than the spectral features and the effects of image spatial resolution on model performance and transferability decrease with increasing plant wetness under irrigation treatment, it can be concluded that all the UAV images acquired in this study with different resolutions could achieve good predictions and transferability of the nitrogen content of winter wheat plants. Full article
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<p>Study site and the spatial distribution of the experiment plot. W0: Rainfed; W1: Irrigated.</p>
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<p>Flowchart of the transferability evaluation for plant nitrogen content.</p>
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<p>Plots of CARS variable selection for the sensitive characteristics of nitrogen content in winter wheat plant. (<b>a</b>) The number of selected plant nitrogen content sensitive features changed as the number of iterations; (<b>b</b>) the RMSECV values changed as the number of iterations.</p>
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<p>The scatterplots between the measured and predicted nitrogen values. (<b>a</b>) 0.01 m resolution; (<b>b</b>) 0.02 m resolution; (<b>c</b>) 0.05 m resolution.</p>
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<p>One-way ANOVA of predictive nitrogen content in winter wheat plants from different resolution image features.</p>
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<p>Transferring nitrogen prediction models constructed with 0.01 m resolution image features to 0.02 m (<b>a</b>) and 0.05 m (<b>b</b>) resolutions.</p>
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<p>Transferring nitrogen prediction models constructed with 0.05 m resolution image features to 0.01 m (<b>a</b>) and 0.02 m (<b>b</b>) resolutions.</p>
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<p>Pixel characteristics of 0.01 m (<b>a</b>), 0.02 m (<b>b</b>), 0.05 m (<b>c</b>) resolution images under W0 and W1 treatments.</p>
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<p>Histogram of the optimized features at different resolutions.</p>
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<p>Plots of CARS variable selection for the sensitive characteristics of nitrogen content in the winter wheat plant based on the three-resolution image features. (<b>A</b>): 0.01 m; (<b>B</b>): 0.02 m; (<b>C</b>): 0.05 m. (<b>a</b>) The number of selected plant nitrogen content sensitive features changed as the number of iterations; (<b>b</b>) the RMSECV values changed as the number of iterations.</p>
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<p>Relationship between the predicted and observed canopy N content for the validation datasets. (<b>A</b>): 0.01 m; (<b>B</b>): 0.02 m; (<b>C</b>): 0.05 m.</p>
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22 pages, 2636 KiB  
Article
A Virtual Point-Oriented Control for Distance-Based Directed Formation and Its Application to Small Fixed-Wing UAVs
by Jiarun Yan, Yangguang Yu, Yinbo Xu and Xiangke Wang
Drones 2022, 6(10), 298; https://doi.org/10.3390/drones6100298 - 12 Oct 2022
Cited by 3 | Viewed by 1803
Abstract
This paper proposes a new algorithm to solve the control problem for a special class of distance-based directed formations, namely directed-triangulated Laman graphs. The central idea of the algorithm is to construct a virtual point for the agents who have more than two [...] Read more.
This paper proposes a new algorithm to solve the control problem for a special class of distance-based directed formations, namely directed-triangulated Laman graphs. The central idea of the algorithm is to construct a virtual point for the agents who have more than two neighbors by employing the information of the desired formation. Compared with the existing methods, the proposed algorithm can make the distance error between the agents converge faster and the path consumption is less. Furthermore, the proposed algorithm is modified to be operable for the small fixed-wing UAV model with nonholonomic and input constraints. Finally, the effectiveness of the proposed method is verified by a series of simulation experiments. Full article
(This article belongs to the Special Issue Multi-UAVs Control)
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<p>The examples of 2D and 3D directed graphs. (<b>a</b>) An example of the 2D directed graph. (<b>b</b>) An example of the 3D directed graph.</p>
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<p>Persistence of the directed graphs. (<b>a</b>) The graph is not constraint-consistent because agent 3 has too many constraints to satisfy. Hence, the graph is not persistent. (<b>b</b>) The graph is constraint-consistent and persistent.</p>
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<p>Constructing a directed-triangulated Laman graph in 2D. (<b>a</b>) Primitive LFF structure. (<b>b</b>) Constructing a new triangulated Laman graph using the directed vertex addition procedure.</p>
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<p>An example of the reflection of the desired formation in 2D. (<b>a</b>) Desired formation. (<b>b</b>) Reflected formation.</p>
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<p>A formation of <span class="html-italic">n</span> agents <math display="inline"><semantics> <mrow> <mo>(</mo> <mi>n</mi> <mo>&gt;</mo> <mn>3</mn> <mo>)</mo> </mrow> </semantics></math> using a directed-triangulated Laman graph.</p>
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<p>A example of agents 1 and 2 remain stationary at the desired distances and agent 3 is controlled to achieve the desired formation.</p>
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<p>A graphical illustration of Algorithm 1.</p>
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<p>The structure diagram of the interconnected system.</p>
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<p>An example of the coordinate system establishment for agent <span class="html-italic">i</span>.</p>
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<p>The overall distributed control framework for <math display="inline"><semantics> <mrow> <mi>n</mi> <mo>&gt;</mo> <mn>3</mn> </mrow> </semantics></math>.</p>
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<p>The illustrations for <math display="inline"><semantics> <msub> <mi>h</mi> <mi>i</mi> </msub> </semantics></math> and <math display="inline"><semantics> <msubsup> <mi>h</mi> <mi>i</mi> <mo>⊥</mo> </msubsup> </semantics></math>.</p>
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<p>The illustrations of the modification of the proposed control law <math display="inline"><semantics> <msub> <mi>u</mi> <mi>i</mi> </msub> </semantics></math> using the projec- tion vectors.</p>
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<p>Comparison Experiment 1: The trajectories of agents.</p>
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<p>Comparison Experiment 1: Distance errors <math display="inline"><semantics> <msub> <mi>e</mi> <mn>31</mn> </msub> </semantics></math> and <math display="inline"><semantics> <msub> <mi>e</mi> <mn>32</mn> </msub> </semantics></math>. (<b>a</b>) Gradient control. (<b>b</b>) Sliding mode. (<b>c</b>) SDRE method. (<b>d</b>) The proposed method.</p>
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<p>Comparison Experiment 2: The trajectories of the agents controlled by different control laws.</p>
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<p>Comparison Experiment 2: Distance errors <math display="inline"><semantics> <msub> <mi>e</mi> <mn>31</mn> </msub> </semantics></math> and <math display="inline"><semantics> <msub> <mi>e</mi> <mn>32</mn> </msub> </semantics></math>. (<b>a</b>) Gradient control. (<b>b</b>) Sliding mode. (<b>c</b>) SDRE method. (<b>d</b>) The proposed method.</p>
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<p>The desired formation <math display="inline"><semantics> <msup> <mrow> <mi mathvariant="script">F</mi> </mrow> <mo>*</mo> </msup> </semantics></math> in comparison experiment 3.</p>
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<p>Comparison Experiment 3 (the colinear case): The trajectories of the agents controlled by four control laws. (<b>a</b>) Gradient control. (<b>b</b>) Sliding mode. (<b>c</b>) SDRE method. (<b>d</b>) The proposed method.</p>
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<p>Comparison Experiment 3 (the colinear case): Distance errors for the proposed method. (<b>a</b>) SDRE method. (<b>b</b>) The proposed method.</p>
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<p>Comparison Experiment 3 (the reflected case): The trajectories of the agents controlled by four control laws. (<b>a</b>) Gradient control. (<b>b</b>) Sliding mode. (<b>c</b>) SDRE method. (<b>d</b>) The proposed method.</p>
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<p>Comparison Experiment 3 (the reflected case): Distance errors for the proposed method.</p>
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<p>The desired formation <math display="inline"><semantics> <msup> <mrow> <mi mathvariant="script">F</mi> </mrow> <mo>*</mo> </msup> </semantics></math> in 3D.</p>
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<p>The results of the simulation. (<b>a</b>) Agent trajectories. (<b>b</b>) Distance errors <math display="inline"><semantics> <msub> <mi>e</mi> <mrow> <mi>i</mi> <mi>j</mi> </mrow> </msub> </semantics></math>, <math display="inline"><semantics> <mrow> <mo>(</mo> <mi>i</mi> <mo>,</mo> <mi>j</mi> <mo>)</mo> <mo>∈</mo> <mi mathvariant="script">E</mi> </mrow> </semantics></math>.</p>
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<p>The desired formation <math display="inline"><semantics> <msup> <mrow> <mi mathvariant="script">F</mi> </mrow> <mo>*</mo> </msup> </semantics></math> of five small fixed-wing UAVs.</p>
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<p>The results of the simulation. (<b>a</b>) Agent trajectories. (<b>b</b>) Distance errors <math display="inline"><semantics> <msub> <mi>e</mi> <mrow> <mi>i</mi> <mi>j</mi> </mrow> </msub> </semantics></math>, <math display="inline"><semantics> <mrow> <mo>(</mo> <mi>i</mi> <mo>,</mo> <mi>j</mi> <mo>)</mo> <mo>∈</mo> <mi mathvariant="script">E</mi> </mrow> </semantics></math>. (<b>c</b>) Linear velocities <math display="inline"><semantics> <msub> <mi>v</mi> <mi>i</mi> </msub> </semantics></math>. (<b>d</b>) Angular velocities <math display="inline"><semantics> <msub> <mi>ω</mi> <mi>i</mi> </msub> </semantics></math>.</p>
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18 pages, 5761 KiB  
Article
Crystal Structure Optimization with Deep-Autoencoder-Based Intrusion Detection for Secure Internet of Drones Environment
by Khalid A. Alissa, Saud S. Alotaibi, Fatma S. Alrayes, Mohammed Aljebreen, Sana Alazwari, Hussain Alshahrani, Mohamed Ahmed Elfaki, Mahmoud Othman and Abdelwahed Motwakel
Drones 2022, 6(10), 297; https://doi.org/10.3390/drones6100297 - 10 Oct 2022
Cited by 11 | Viewed by 2187
Abstract
Drone developments, especially small-sized drones, usher in novel trends and possibilities in various domains. Drones offer navigational inter-location services with the involvement of the Internet of Things (IoT). On the other hand, drone networks are highly prone to privacy and security risks owing [...] Read more.
Drone developments, especially small-sized drones, usher in novel trends and possibilities in various domains. Drones offer navigational inter-location services with the involvement of the Internet of Things (IoT). On the other hand, drone networks are highly prone to privacy and security risks owing to their strategy flaws. In order to achieve the desired efficiency, it is essential to create a secure network. The purpose of the current study is to have an overview of the privacy and security problems that recently impacted the Internet of Drones (IoD). An Intrusion Detection System (IDS) is an effective approach to determine the presence of intrusions in the IoD environment. The current study focuses on the design of Crystal Structure Optimization with Deep-Autoencoder-based Intrusion Detection (CSODAE-ID) for a secure IoD environment. The aim of the presented CSODAE-ID model is to identify the occurrences of intrusions in IoD environment. In the proposed CSODAE-ID model, a new Modified Deer Hunting Optimization-based Feature Selection (MDHO-FS) technique is applied to choose the feature subsets. At the same time, the Autoencoder (AE) method is employed for the classification of intrusions in the IoD environment. The CSO algorithm, inspired by the formation of crystal structures based on the lattice points, is employed at last for the hyperparameter-tuning process. To validate the enhanced performance of the proposed CSODAE-ID model, multiple simulation analyses were performed and the outcomes were assessed under distinct aspects. The comparative study outcomes demonstrate the superiority of the proposed CSODAE-ID model over the existing techniques. Full article
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<p>Overall process of CSODAE-ID algorithm.</p>
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<p>Flowchart of DHO algorithm.</p>
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<p>Confusion matrices of CSODAE-ID approach. (<b>a</b>) Entire dataset, (<b>b</b>) 70% of TR data, and (<b>c</b>) 30% of TS data.</p>
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<p>Results of the analysis of CSODAE-ID approach on entire dataset.</p>
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<p>Results of the analysis of CSODAE-ID approach on 70% of TR data.</p>
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<p>Results of the analysis of CSODAE-ID approach on 30% of TS data.</p>
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<p>TRA and VLA analyses results of CSODAE-ID methodology.</p>
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<p>TRL and VLL analyses results of CSODAE-ID methodology.</p>
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<p>Precision–recall analysis results of CSODAE-ID methodology.</p>
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<p>ROC analysis results of CSODAE-ID methodology.</p>
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<p><math display="inline"><semantics> <mrow> <mi>A</mi> <mi>c</mi> <mi>c</mi> <msub> <mi>u</mi> <mi>y</mi> </msub> </mrow> </semantics></math> and <math display="inline"><semantics> <mrow> <mi>F</mi> <msub> <mn>1</mn> <mrow> <mi>s</mi> <mi>c</mi> <mi>o</mi> <mi>r</mi> <mi>e</mi> </mrow> </msub> </mrow> </semantics></math> analyses results of CSODAE-ID approach and other existing methodologies.</p>
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<p><math display="inline"><semantics> <mrow> <mi>P</mi> <mi>r</mi> <mi>e</mi> <msub> <mi>c</mi> <mi>n</mi> </msub> </mrow> </semantics></math> and <math display="inline"><semantics> <mrow> <mi>R</mi> <mi>e</mi> <mi>c</mi> <msub> <mi>a</mi> <mi>l</mi> </msub> </mrow> </semantics></math> analyses results of CSODAE-ID approach and other existing methodologies.</p>
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14 pages, 1952 KiB  
Article
Elliptical Multi-Orbit Circumnavigation Control of UAVS in Three-Dimensional Space Depending on Angle Information Only
by Zhen Wang and Yanhong Luo
Drones 2022, 6(10), 296; https://doi.org/10.3390/drones6100296 - 10 Oct 2022
Cited by 3 | Viewed by 2280
Abstract
In order to analyze the circumnavigation tracking problem in complex three-dimensional space, in this paper, we propose a UAV group circumnavigation control strategy, in which the UAV circumnavigation orbit is an ellipse whose size can be adjusted arbitrarily; at the same time, the [...] Read more.
In order to analyze the circumnavigation tracking problem in complex three-dimensional space, in this paper, we propose a UAV group circumnavigation control strategy, in which the UAV circumnavigation orbit is an ellipse whose size can be adjusted arbitrarily; at the same time, the UAV group can be assigned to multiple orbits for tracking. The UAVs only have the angle information of the target, and the position information of the target can be obtained by using the angle information and the proposed three-dimensional estimator, thereby establishing an ideal relative velocity equation. By constructing the error dynamic equation between the actual relative velocity and the ideal relative velocity, the circumnavigation problem in three-dimensional space is transformed into a velocity tracking problem. Since the UAVs are easily disturbed by external factors during flight, the sliding mode control is used to improve the robustness of the system. Finally, the effectiveness of the control law and its robustness to unexpected situations are verified by simulation. Full article
(This article belongs to the Special Issue Advances in UAV Detection, Classification and Tracking)
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<p>Schematic diagram of three-dimensional space circumnavigation.</p>
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<p>Top view of circumnavigation.</p>
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<p>Multi-orbit circumnavigation.</p>
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<p>Quadcopter UAV coordinate system.</p>
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<p>Top view of the UAV <span class="html-italic">i</span> at time <span class="html-italic">t</span>.</p>
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<p>Position estimator error convergence <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mover accent="true"> <mi mathvariant="bold-italic">p</mi> <mo stretchy="false">^</mo> </mover> <mi mathvariant="bold-italic">ti</mi> </msub> <mo>−</mo> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">t</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> </mrow> </semantics></math>.</p>
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<p>Angular spacing between adjacent UAVs.</p>
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<p>Circumnavigation control error. (<b>a</b>) <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">i</mi> </msub> <mo>−</mo> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">t</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> </mrow> </semantics></math>. (<b>b</b>) <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">i</mi> </msub> <mo>−</mo> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">t</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <mo>−</mo> <msub> <mi>τ</mi> <mi>i</mi> </msub> <msub> <mi>l</mi> <mi>d</mi> </msub> </mrow> </semantics></math>.</p>
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<p>Three−dimensional diagram of circumnavigation control.</p>
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<p>Variation in angular separation between adjacent UAVs when interference occurs.</p>
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<p>The circumnavigation control error when disturbance occurs. (<b>a</b>) <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">i</mi> </msub> <mo>−</mo> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">t</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> </mrow> </semantics></math>. (<b>b</b>) <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">i</mi> </msub> <mo>−</mo> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">t</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <mo>−</mo> <msub> <mi>τ</mi> <mi>i</mi> </msub> <msub> <mi>l</mi> <mi>d</mi> </msub> </mrow> </semantics></math>.</p>
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<p>Position estimator error convergence <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mover accent="true"> <mi mathvariant="bold-italic">p</mi> <mo stretchy="false">^</mo> </mover> <mi mathvariant="bold-italic">ti</mi> </msub> <mo>−</mo> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">t</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> </mrow> </semantics></math>.</p>
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<p>Angular spacing between adjacent UAVs.</p>
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<p>Circumnavigation control error. (<b>a</b>) <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">i</mi> </msub> <mo>−</mo> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">t</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> </mrow> </semantics></math>. (<b>b</b>) <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">i</mi> </msub> <mo>−</mo> <msub> <mi mathvariant="bold-italic">p</mi> <mi mathvariant="bold-italic">t</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <mo>−</mo> <msub> <mi>τ</mi> <mi>i</mi> </msub> <msub> <mi>l</mi> <mi>d</mi> </msub> </mrow> </semantics></math>.</p>
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<p>Three−dimensional diagram of circumnavigation control.</p>
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<p>Variation in angular separation between adjacent UAVs when interference occurs.</p>
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<p>The circumnavigation control error when disturbance occurs. (<b>a</b>) <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mi>p</mi> <mi>i</mi> </msub> <mo>−</mo> <msub> <mi>p</mi> <mi>t</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> </mrow> </semantics></math>. (<b>b</b>) <math display="inline"><semantics> <mrow> <mrow> <mo>|</mo> <mo>|</mo> </mrow> <msub> <mi>p</mi> <mi>i</mi> </msub> <mo>−</mo> <msub> <mi>p</mi> <mi>t</mi> </msub> <mo>−</mo> <msub> <mi>τ</mi> <mi>i</mi> </msub> <msub> <mi>l</mi> <mi>d</mi> </msub> <mrow> <mo>|</mo> <mo>|</mo> </mrow> </mrow> </semantics></math>.</p>
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17 pages, 2452 KiB  
Article
Sliding Mode Disturbance Observer-Based Adaptive Dynamic Inversion Fault-Tolerant Control for Fixed-Wing UAV
by Zhe Dong, Kai Liu and Shipeng Wang
Drones 2022, 6(10), 295; https://doi.org/10.3390/drones6100295 - 10 Oct 2022
Cited by 10 | Viewed by 2894
Abstract
Unmanned aerial vehicles (UAVs) have been widely applied over the past decades, especially in the military field. Due to the unpredictability of the flight environment and failures, higher requirements are placed on the design of the control system of the fixed-wing UAV. In [...] Read more.
Unmanned aerial vehicles (UAVs) have been widely applied over the past decades, especially in the military field. Due to the unpredictability of the flight environment and failures, higher requirements are placed on the design of the control system of the fixed-wing UAV. In this study, a sliding mode disturbance observer-based (SMDO) adaptive dynamic inversion fault-tolerant controller was designed, which includes an outer-loop sliding mode observer-based disturbance suppression dynamic inversion controller and an inner-loop real-time aerodynamic identification-based adaptive fault-tolerant dynamic inversion controller. The sliding mode disturbance observer in the outer-loop controller was designed based on the second-order super-twisting algorithm to alleviate chattering. The aerodynamic identification in the inner-loop controller adopts the recursive least squares algorithm to update the aerodynamic model of the UAV online, thereby realizing the fault-tolerant control for the control surface damage. The effectiveness of the proposed SMDO enhanced adaptive fault-tolerant control method was validated by mathematical simulation. Full article
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<p>Sliding mode disturbance observer-based nonlinear dynamic inversion (SMDO-NDI) control structure flow diagram.</p>
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<p>Adaptive disturbance suppression integrated controller (ADSIC) control structure flow diagram.</p>
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<p>Recursive least squares-based aerodynamic identification flow diagram.</p>
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<p>Simulation comparison of angle control under elevator surface structural failure. (<b>a</b>) The illustration of the difference between adaptive NDI and conventional NDI in command tracking under the condition of elevator failure. (<b>b</b>) Pitch angle tracking error under the two control methods. (<b>c</b>) The illustration of the change in the angle of attack when adaptive NDI and conventional NDI are controlled separately.</p>
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<p>Simulation comparison of angle control under elevator surface structural failure. (<b>a</b>) The illustration of the difference between adaptive NDI and conventional NDI in command tracking under the condition of elevator failure. (<b>b</b>) Pitch angle tracking error under the two control methods. (<b>c</b>) The illustration of the change in the angle of attack when adaptive NDI and conventional NDI are controlled separately.</p>
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<p>Simulation result of elevator efficiency identification.</p>
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<p>Comparison of elevator simulation and angular rate simulation under conventional NDI and adaptive NDI control. (<b>a</b>) Elevator deflection curves under conventional NDI and adaptive NDI control. (<b>b</b>) Angular rate variation curves under conventional NDI and adaptive NDI control.</p>
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<p>Simulation comparison of pitch angle control under composite disturbance. (<b>a</b>) The illustration of the difference between adaptive NDI and ADSIC under composite disturbance. (<b>b</b>) Pitch angle tracking error under the two control methods.</p>
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<p>Simulation of key variables in attitude control. (<b>a</b>) Elevator deflection curves under adaptive nonlinear dynamic inversion (ANDI) and ADSIC control. (<b>b</b>) Angular rate variation curves under ANDI and ADSIC control. (<b>c</b>) Simulation of sliding mode observer’s estimation of compound disturbance.</p>
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<p>Simulation of key variables in attitude control. (<b>a</b>) Elevator deflection curves under adaptive nonlinear dynamic inversion (ANDI) and ADSIC control. (<b>b</b>) Angular rate variation curves under ANDI and ADSIC control. (<b>c</b>) Simulation of sliding mode observer’s estimation of compound disturbance.</p>
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19 pages, 3834 KiB  
Article
The Bathy-Drone: An Autonomous Uncrewed Drone-Tethered Sonar System
by Antonio L. Diaz, Andrew E. Ortega, Henry Tingle, Andres Pulido, Orlando Cordero, Marisa Nelson, Nicholas E. Cocoves, Jaejeong Shin, Raymond R. Carthy, Benjamin E. Wilkinson and Peter G. Ifju
Drones 2022, 6(10), 294; https://doi.org/10.3390/drones6100294 - 10 Oct 2022
Cited by 9 | Viewed by 6131
Abstract
A unique drone-based system for underwater mapping (bathymetry) was developed at the University of Florida. The system, called the “Bathy-drone”, comprises a drone that drags, via a tether, a small vessel on the water surface in a raster pattern. The vessel is equipped [...] Read more.
A unique drone-based system for underwater mapping (bathymetry) was developed at the University of Florida. The system, called the “Bathy-drone”, comprises a drone that drags, via a tether, a small vessel on the water surface in a raster pattern. The vessel is equipped with a recreational commercial off-the-shelf (COTS) sonar unit that has down-scan, side-scan, and chirp capabilities and logs GPS-referenced sonar data onboard or transmitted in real time with a telemetry link. Data can then be retrieved post mission and plotted in various ways. The system provides both isobaths and contours of bottom hardness. Extensive testing of the system was conducted on a 5 acre pond located at the University of Florida Plant Science and Education Unit in Citra, FL. Prior to performing scans of the pond, ground-truth data were acquired with an RTK GNSS unit on a pole to precisely measure the location of the bottom at over 300 locations. An assessment of the accuracy and resolution of the system was performed by comparison to the ground-truth data. The pond ground truth had an average depth of 2.30 m while the Bathy-drone measured an average 21.6 cm deeper than the ground truth, repeatable to within 2.6 cm. The results justify integration of RTK and IMU corrections. During testing, it was found that there are numerous advantages of the Bathy-drone system compared to conventional methods including ease of implementation and the ability to initiate surveys from the land by flying the system to the water or placing the platform in the water. The system is also inexpensive, lightweight, and low-volume, thus making transport convenient. The Bathy-drone can collect data at speeds of 0–24 km/h (0–15 mph) and, thus, can be used in waters with swift currents. Additionally, there are no propellers or control surfaces underwater; hence, the vessel does not tend to snag on floating vegetation and can be dragged over sandbars. An area of more than 10 acres was surveyed using the Bathy-drone in one battery charge and in less than 25 min. Full article
(This article belongs to the Special Issue Unconventional Drone-Based Surveying)
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<p>Bathymetry system during autonomous flight for ground-truthing at University of Florida Plant Science Research Citra, Florida. Photo credit: author’s UF UASRP lab.</p>
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<p>Forces at a constant speed on the hull. The center of gravity is labeled CG. Figure credit: author’s UF UASRP lab.</p>
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<p>In a turn, the tether force acts laterally with respect to the hull. The center of gravity is labeled CG. Figure credit: author’s UF UASRP lab.</p>
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<p>Isometric view of the Bathy-drone from the top showing sonar screen through the open hatches (<b>left</b>) and from the bottom with fins and transducer (<b>right</b>). Where RTK GPS is Real Time Kinematics corrected Global Positioning System and IMU is Inertial Measurement Unit. Photo credit: author’s UF UASRP lab.</p>
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<p>The moving rover and the data collector taking topographic points throughout the pond from a barge (<b>left</b> image). Custom 3D printed silt foot for level rod (<b>center</b>). The base station set up on a nail driven into the asphalt (<b>left</b> tripod) and the radio (<b>right</b> tripod) (<b>right</b> image) transmitting the RTK GPS corrections. The base nail was measured for 8 h as static observations and submitted to NOAA OPUS. Topographic points collected across different days were translated so that the base station points aligned with the NOAA OPUS solution. Photo credit: UF UASRP; student researchers pictured on the left image.</p>
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<p>Ground-truthing data consisting of 324 RTK-corrected points with a minimum depth of 0.17 m, maximum of 3.87 m, mean of 2.30 m, and standard deviation of 1.03 m (<b>left</b>). Local polynomial interpolation of the ground-truth data (<b>right</b>). Horizontal coordinates are in NAD 1983 (2011) State Plane Florida West FIPS 0902 (meters) and vertical coordinates are in height above ellipsoid (meters).</p>
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<p>Comparison of GNSS-recorded flight path of multirotor drone and the path of the sonar payload vessel. Photo credit: UF UASRP using satellite imagery.</p>
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<p>Local polynomial interpolation of sonar data from a cross boustrophedon flight pattern at 4.5 mph. Superimposed on photogrammetry data gathered by author’s UF UASRP lab. Photo credit: UF UASRP.</p>
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<p>Bottom hardness as a measure of acoustic backscatter where light colors are softer and darker colors are harder. The bottom hardness color plot is overlayed with isobaths in meters. Superimposed on photogrammetry data gathered by author’s UF UASRP lab.</p>
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<p>Sonar of Canal C-11, bridge pile at Fort Lauderdale Florida, showing accumulated vegetation and scour undermining the pile (<b>A</b>). This shows the potential for the drone bathymetry system to be used for inspection of civil infrastructure. Side-scan sonar of submersed vehicle in a quarry in northern Florida (<b>B</b>). ((<b>C</b>), <b>Left</b>) Sidescan sonar image of tilapia nesting beds captured at the Citra retention pond compared with photogrammetry ((<b>C</b>), <b>Right</b>). Photo credit: UF UASRP.</p>
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<p>Residuals (m) between local polynomial interpolation of combined sonar transects and ground-truth data obtained from the Real Time Kinematics (RTK) corrected graduated rod measurements. Positive residuals indicate that sonar readings are deeper than ground truth. The size of the points corresponds with the residual magnitude, and the color corresponds with the direction. Photo credit: UF UASRP using satellite imagery.</p>
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<p>Histogram and summary statistics of residuals where the mean is 21.6 cm, the median is 18.7 cm, and the standard deviation is 16.7 cm (<b>left</b>). Scatterplot of residuals and the relationship with depth, where the blue dash linear line of best fit demonstrates decreasing residual with decreasing depth (<b>right</b>).</p>
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<p>Visualization of east–west interpolated surface versus that of north–south transects. The mean residual is −2.64 cm, the median is 0.95 cm, and the standard deviation is 16.98 cm. The stars labeled “intersection” are example calculation locations for the depth difference between NS and EW. Photo credit: UF UASRP using satellite imagery.</p>
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<p>Depth values of the data values shown in red in <a href="#drones-06-00294-f013" class="html-fig">Figure 13</a> on the upper star and lower star, respectively. The point where the two intersect is shown (black line). The difference for the left plot is 14.9 cm, and the difference for right plot is −1.69 cm.</p>
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<p>Histogram (blue) of precision analysis: difference of depth measurements at the intersections of NS and EW lawnmower paths.</p>
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21 pages, 6077 KiB  
Article
UAV Charging Station Placement in Opportunistic Networks
by Salih Safa Bacanli, Enas Elgeldawi, Begümhan Turgut and Damla Turgut
Drones 2022, 6(10), 293; https://doi.org/10.3390/drones6100293 - 9 Oct 2022
Cited by 11 | Viewed by 3246
Abstract
Unmanned aerial vehicles (UAVs) are now extensively used in a wide variety of applications, including a key role within opportunistic wireless networks. These types of opportunistic networks are considered well suited for infrastructure-less areas, or urban areas with overloaded cellular networks. For these [...] Read more.
Unmanned aerial vehicles (UAVs) are now extensively used in a wide variety of applications, including a key role within opportunistic wireless networks. These types of opportunistic networks are considered well suited for infrastructure-less areas, or urban areas with overloaded cellular networks. For these networks, UAVs are envisioned to complement and support opportunistic network performance; however, the short battery life of commercial UAVs and their need for frequent charging can limit their utility. This paper addresses the challenge of charging station placement in a UAV-aided opportunistic network. We implemented three clustering approaches, namely, K-means, Density-Based Spatial Clustering of Applications with Noise (DBSCAN), and random clustering, with each clustering approach being examined in combination with Epidemic, Spray and Wait, and State-Based Campus Routing (SCR) routing protocols. The simulation results show that determining the charging station locations using K-means clustering with three clusters showed lower message delay and higher success rate than deciding the charging station location either randomly or using DBSCAN regardless of the routing strategy employed between nodes. Full article
(This article belongs to the Special Issue UAV IoT Sensing and Networking)
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<p>UAV-aided opportunistic network architecture.</p>
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<p>Archimedes spiral with density d and maximum radius as R.</p>
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<p>Session example in epidemic routing.</p>
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<p>Cumulative distribution function of Message Delay on NCSU Dataset.</p>
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<p>Cumulative distribution function of Message Delay on KAIST Dataset.</p>
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<p>Box plot distribution results of Message Delay on NCSU Dataset.</p>
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<p>Box plot distribution results of Message Delay on KAIST Dataset.</p>
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<p>Distribution results of Success Rate on NCSU Dataset.</p>
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<p>Distribution results of Success Rate on KAIST Dataset.</p>
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<p>Box plot distribution results of Success Rate on NCSU Dataset.</p>
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<p>Box plot distribution results of Success Rate on KAIST Dataset.</p>
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<p>Number of UAV Tours in NCSU Dataset.</p>
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<p>Number of UAV Tours in KAIST Dataset.</p>
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<p>Number of UAV Tours in NCSU Dataset.</p>
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<p>Number of UAV Tours in KAIST Dataset.</p>
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<p>Number of Messages Added to Buffer in NCSU Dataset.</p>
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<p>Number of Messages Added to Buffer in KAIST Dataset.</p>
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24 pages, 20763 KiB  
Article
A Novel Method of Small Object Detection in UAV Remote Sensing Images Based on Feature Alignment of Candidate Regions
by Jinkang Wang, Faming Shao, Xiaohui He and Guanlin Lu
Drones 2022, 6(10), 292; https://doi.org/10.3390/drones6100292 - 7 Oct 2022
Cited by 8 | Viewed by 2667
Abstract
To solve the problem of low detection accuracy of small objects in UAV optical remote sensing images due to low contrast, dense distribution, and weak features, this paper proposes a small object detection method based on feature alignment of candidate regions is proposed [...] Read more.
To solve the problem of low detection accuracy of small objects in UAV optical remote sensing images due to low contrast, dense distribution, and weak features, this paper proposes a small object detection method based on feature alignment of candidate regions is proposed for remote sensing images. Firstly, AFA-FPN (Attention-based Feature Alignment FPN) defines the corresponding relationship between feature mappings, solves the misregistration of features between adjacent levels, and improves the recognition ability of small objects by aligning and fusing shallow spatial features and deep semantic features. Secondly, the PHDA (Polarization Hybrid Domain Attention) module captures local areas containing small object features through parallel channel domain attention and spatial domain attention. It assigns a larger weight to these areas to alleviate the interference of background noise. Then, the rotation branch uses RROI to rotate the horizontal frame obtained by RPN, which avoids missing detection of small objects with dense distribution and arbitrary direction. Next, the rotation branch uses RROI to rotate the horizontal box obtained by RPN. It solves the problem of missing detection of small objects with dense distribution and arbitrary direction and prevents feature mismatch between the object and candidate regions. Finally, the loss function is improved to better reflect the difference between the predicted value and the ground truth. Experiments are conducted on a self-made dataset. The experimental results show that the mAP of the proposed method reaches 82.04% and the detection speed reaches 24.3 FPS, which is significantly higher than that of the state-of-the-art methods. Meanwhile, the ablation experiment verifies the rationality of each module. Full article
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<p>The pipelines of the proposed method.</p>
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<p>The structure of the AFA-FPN module.</p>
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<p>The flow chart of the AFA-FPN module.</p>
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<p>The structure of the PHDA module.</p>
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<p>The flow chart of RRoI rotation position-sensitive pooling.</p>
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<p>The schematic diagram of the two-stage box rotation process of the rotation branch.</p>
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<p>Some image examples from the RSSO dataset.</p>
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<p>Comparison of P-R curves of small, medium, and large objects and all objects.</p>
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<p>Comparison of the P-R curves of adopting different backbone networks.</p>
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<p>Visualization of the detection performance between our proposed method and the state-of-the-art methods in simple background.</p>
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<p>Visualization of the detection performance between our proposed method and the state-of-the-art methods in a complex background.</p>
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<p>Visualization of the detection performance between our proposed method and the state-of-the-art methods for multi-scale object detection.</p>
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<p>Visualization of the detection performance between our proposed method and the state-of-the-art methods for the detection of densely distributed small objects.</p>
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<p>Visualization of the detection performance of our proposed method for multi-scale objects on high-resolution remote sensing images of large scenes.</p>
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<p>Visualization of the detection performance of our proposed method on other remote sensing image examples.</p>
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17 pages, 3034 KiB  
Article
Aerial Drone Surveys Reveal the Efficacy of a Protected Area Network for Marine Megafauna and the Value of Sea Turtles as Umbrella Species
by Liam C. D. Dickson, Stuart R. B. Negus, Christophe Eizaguirre, Kostas A. Katselidis and Gail Schofield
Drones 2022, 6(10), 291; https://doi.org/10.3390/drones6100291 - 7 Oct 2022
Cited by 8 | Viewed by 4087
Abstract
Quantifying the capacity of protected area networks to shield multiple marine megafauna with diverse life histories is complicated, as many species are wide-ranging, requiring varied monitoring approaches. Yet, such information is needed to identify and assess the potential use of umbrella species and [...] Read more.
Quantifying the capacity of protected area networks to shield multiple marine megafauna with diverse life histories is complicated, as many species are wide-ranging, requiring varied monitoring approaches. Yet, such information is needed to identify and assess the potential use of umbrella species and to plan how best to enhance conservation strategies. Here, we evaluated the effectiveness of part of the European Natura 2000 protected area network (western Greece) for marine megafauna and whether loggerhead sea turtles are viable umbrella species in this coastal region. We systematically surveyed inside and outside coastal marine protected areas (MPAs) at a regional scale using aerial drones (18,505 animal records) and combined them with distribution data from published datasets (tracking, sightings, strandings) of sea turtles, elasmobranchs, cetaceans and pinnipeds. MPAs covered 56% of the surveyed coastline (~1500 km). There was just a 22% overlap in the distributions of the four groups from aerial drone and other datasets, demonstrating the value of combining different approaches to improve records of coastal area use for effective management. All four taxonomic groups were more likely to be detected inside coastal MPAs than outside, confirming sufficient habitat diversity despite varied life history traits. Coastal habitats frequented by loggerhead turtles during breeding/non-breeding periods combined overlapped with 76% of areas used by the other three groups, supporting their potential use as an umbrella species. In conclusion, this study showed that aerial drones can be readily combined with other monitoring approaches in coastal areas to enhance the management of marine megafauna in protected area networks and to identify the efficacy of umbrella species. Full article
(This article belongs to the Special Issue Drones for Biodiversity Conservation)
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<p>Study region including the Natura 2000 protected area network (shaded blue polygons). Inset map shows study area within the wider Mediterranean. Red star: Gulf of Argostoli; Red triangle: Laganas Bay; Red lines show coastal limits of aerial drone surveys; Kato Korogona in the south to Kalogria in the north. Surveys spanned 0–400 m offshore.</p>
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<p>(<b>a</b>) Study region showing the distribution of the four key habitat types inside and outside MPAs. Natura 2000 MPAs: shaded blue polygons. Circles represent 2 km cells along coastline. (<b>b</b>) Total number of cells represented by each habitat type inside (grey) and outside (black) MPAs.</p>
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<p>(<b>a</b>) Study region showing the loggerhead sea turtles (<span class="html-italic">Caretta caretta</span>) recorded in aerial drone surveys and tracking datasets and both aerial and tracking datasets (for each approach separately see <a href="#app1-drones-06-00291" class="html-app">Figure S1</a>). Natura 2000 MPAs: shaded blue polygons. Circles represent 2 km cells along the coastline. (<b>b</b>) Loggerhead sea turtles recorded in cells for aerial drone surveys (white bars) versus tracking datasets (grey bars) during the combined breeding/non-breeding period, the breeding period and the non-breeding period. (<b>c</b>) Number of cells containing loggerhead sea turtles of different densities for aerial drone surveys (white bars) and tracking datasets (grey bars) (<a href="#app1-drones-06-00291" class="html-app">Table S1</a>). Red lines in (<b>b</b>) and (<b>c</b>) show the number of cells for which tracking and aerial drone surveys overlap.</p>
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<p>(<b>a</b>) Study region showing where loggerhead sea turtles (<span class="html-italic">Caretta caretta</span>) were recorded during the breeding period, non-breeding period and both periods combined. Data are integrated from aerial drone surveys and the published literature (<a href="#app1-drones-06-00291" class="html-app">Table S1</a>). <a href="#app1-drones-06-00291" class="html-app">Figure S2</a> presents separate breeding and non-breeding distributions. (<b>b</b>) Loggerhead sea turtles recorded in cells during the breeding period and non-breeding period inside (white bars) and outside (grey bars) MPAs. The number of overlapping breeding/non-breeding cells is shown by a red line. (<b>c</b>) Number of cells of each habitat type over which loggerhead sea turtles were recorded in each period inside (white bars) and outside (grey bars) MPAs for overlapping breeding/non-breeding period cells (the same trends were obtained for all breeding period only cells and non-breeding period only cells; <a href="#app1-drones-06-00291" class="html-app">Figure S5b,e</a>). Aerial drone images of sea turtles (<b>d</b>) over submerged sandbanks during the breeding period, and (<b>e</b>) over vegetated substrate during the non-breeding period. Sea turtles are circled in black. Enlarged circles show turtles at 5× magnification. Natura 2000 MPAs: shaded blue polygons. Circles represent 2 km cells along the coastline. Blue rectangle represents Gulf of Argostoli (Kefalonia), which supports year-round non-breeding habitat (for density and habitat type see <a href="#app1-drones-06-00291" class="html-app">Figures S5c,f and S6</a>).</p>
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<p>(<b>a</b>) Number of taxa found in each cell across the study region (<a href="#app1-drones-06-00291" class="html-app">Figures S6 and S7</a> for each taxon separately). Natura 2000 MPAs: shaded blue polygons. Aerial drone images of (<b>b</b>) Cuvier’s beaked whale (<span class="html-italic">Ziphius cavirostris</span>) sighted at 100 m from shore; (<b>c</b>) sharks sighted at 400 m from shore. Enlarged circles show the animals at 5× magnification.</p>
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<p>Number of taxa (<b>a</b>) inside (white bars) and outside (grey bars) MPAs and for (<b>b</b>) each taxon separately. Habitat type of cells containing (<b>c</b>) 0–3 taxa; and (<b>d</b>) each taxon separately for the entire study region. White, vegetated; light grey, submerged sandbanks; dark grey, rocky outcrops and reefs; black, mud/silt.</p>
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<p>(<b>a</b>) Number of kilometres of coastline inside MPAs capturing taxa based on five scenarios: (1) all cells with one or more taxa (baseline); (2) all cells containing breeding turtles; (3) all cells containing non-breeding loggerhead turtles; (4) all cells containing combined breeding and non-breeding loggerhead turtles; (5) just overlapping cells containing breeding/non-breeding loggerhead turtles (combined). Black: 3 taxa cells; dark grey: 2 taxa cells; light grey: 1 taxon cells; (<b>b</b>) Number of additional kilometres required to extend protection effort outside MPAs based on the same five scenarios.</p>
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12 pages, 3256 KiB  
Article
A Human-Detection Method Based on YOLOv5 and Transfer Learning Using Thermal Image Data from UAV Perspective for Surveillance System
by Aprinaldi Jasa Mantau, Irawan Widi Widayat, Jenq-Shiou Leu and Mario Köppen
Drones 2022, 6(10), 290; https://doi.org/10.3390/drones6100290 - 4 Oct 2022
Cited by 24 | Viewed by 6770
Abstract
At this time, many illegal activities are being been carried out, such as illegal mining, hunting, logging, and forest burning. These things can have a substantial negative impact on the environment. These illegal activities are increasingly rampant because of the limited number of [...] Read more.
At this time, many illegal activities are being been carried out, such as illegal mining, hunting, logging, and forest burning. These things can have a substantial negative impact on the environment. These illegal activities are increasingly rampant because of the limited number of officers and the high cost required to monitor them. One possible solution is to create a surveillance system that utilizes artificial intelligence to monitor the area. Unmanned aerial vehicles (UAV) and NVIDIA Jetson modules (general-purpose GPUs) can be inexpensive and efficient because they use few resources. The problem from the object-detection field utilizing the drone’s perspective is that the objects are relatively small compared to the observation space, and there are also illumination and environmental challenges. In this study, we will demonstrate the use of the state-of-the-art object-detection method you only look once (YOLO) v5 using a dataset of visual images taken from a UAV (RGB-image), along with thermal infrared information (TIR), to find poachers. There are seven scenario training methods that we have employed in this research with RGB and thermal infrared data to find the best model that we will deploy on the Jetson Nano module later. The experimental result shows that a new model with pre-trained model transfer learning from the MS COCO dataset can improve YOLOv5 to detect the human–object in the RGBT image dataset. Full article
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<p>UAVs with NVIDIA Jetson Nano for surveillance system.</p>
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<p>Wavelength of light.</p>
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<p>Jetson Nano module.</p>
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<p>YOLOv5 architecture. Backbone: CSPD; neck: PANet; and head: YOLO layer detection results (class, score, location, and size).</p>
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<p>RGBT VisDrone crowd-counting dataset [<a href="#B25-drones-06-00290" class="html-bibr">25</a>].</p>
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<p>Model search and human–object detection on Jetson Nano workflow.</p>
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<p>YOLOv5s original model detection result. (<b>a</b>) TIR Image. (<b>b</b>) RGB Image.</p>
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<p>YOLOv5-RGB model detection result. (<b>a</b>) TIR Image. (<b>b</b>) RGB Image.</p>
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<p>YOLOv5-TIR model detection result. (<b>a</b>) TIR Image. (<b>b</b>) RGB Image.</p>
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<p>YOLOv5-RGBT detection result. (<b>a</b>) TIR Image. (<b>b</b>) RGB Image.</p>
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12 pages, 20895 KiB  
Article
Wind Speed Measurement by an Inexpensive and Lightweight Thermal Anemometer on a Small UAV
by Jun Inoue and Kazutoshi Sato
Drones 2022, 6(10), 289; https://doi.org/10.3390/drones6100289 - 3 Oct 2022
Cited by 9 | Viewed by 7279
Abstract
Profiling wind information when using a small unmanned aerial vehicle (sUAV) is vital for atmospheric profiling and monitoring attitude during flight. Wind speed on an sUAV can be measured directly using ultrasonic anemometers or by calculating its attitude control information. The former method [...] Read more.
Profiling wind information when using a small unmanned aerial vehicle (sUAV) is vital for atmospheric profiling and monitoring attitude during flight. Wind speed on an sUAV can be measured directly using ultrasonic anemometers or by calculating its attitude control information. The former method requires a relatively large payload for an onboard ultrasonic anemometer, while the latter requires real-time flight log data access, which depends on the UAV manufacturers. This study proposes the feasibility of a small thermal anemometer to measure wind speeds inexpensively using a small commercial quadcopter (DJI Mavic2: M2). A laboratory experiment demonstrated that the horizontal wind speed bias increased linearly with ascending sUAV speed. A smoke experiment during hovering revealed the downward wind bias (1.2 m s1) at a 12-cm height above the M2 body. Field experiments in the ice-covered ocean demonstrated that the corrected wind speed agreed closely with the shipboard wind data observed by a calibrated ultrasonic anemometer. A dual-mount system comprising thermal anemometers was proposed to measure wind speed and direction. Full article
(This article belongs to the Special Issue Unmanned Aerial Vehicles in Atmospheric Research)
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<p>(<b>a</b>) HWS-19-ONE, (<b>b</b>) top view, (<b>c</b>) front view, and (<b>d</b>) rear view of Mavic2 Enterprise Dual with all onboard sensors.</p>
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<p>(<b>a</b>) Horizontal wind experiments, and (<b>b</b>) vertical wind experiments.</p>
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<p>Scatter plot of wind speed by ultrasonic anemometers (WXT536 &amp; WS500: <span class="html-italic">W</span>) and HWS (<math display="inline"><semantics> <msub> <mi>U</mi> <mrow> <mi>o</mi> <mi>b</mi> <mi>s</mi> </mrow> </msub> </semantics></math>).</p>
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<p>(<b>a</b>) Setup of smoke experiment, and (<b>b</b>) front view and (<b>c</b>) side view of the hovering M2 with visualization by a smoke and laser system.</p>
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<p>Results of smoke experiments. (<b>a</b>–<b>d</b>) Raw images and (<b>e</b>–<b>h</b>) analyzed velocity fields for each experiment. Magenta arrows indicate the target location where the HWS is installed.</p>
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<p>Relationships between observed wind speed by the HWS and corrected horizontal wind speed proposed by Equation (<a href="#FD2-drones-06-00289" class="html-disp-formula">2</a>). Each color indicated the case of ascending speed.</p>
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<p>(<b>a</b>) Cruise map of PV <span class="html-italic">Soya</span> with the MODIS image on 10 February 2022 and the M2 profiling stations (yellow dots), (<b>b</b>) locations of the M2 operation and the ultrasonic anemometer (WXT536), and (<b>c</b>) the closeup image of WXT536 on the upper deck of the ship.</p>
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<p>(<b>a</b>) Time–height cross section of the corrected wind speed obtained by the M2, and (<b>b</b>) time series of horizontal wind speed observed by PV <span class="html-italic">Soya</span> (black: ship speed &gt; 1 m s<math display="inline"><semantics> <msup> <mrow/> <mrow> <mo>−</mo> <mn>1</mn> </mrow> </msup> </semantics></math>, gray: ship speed ≤ 1 m s<math display="inline"><semantics> <msup> <mrow/> <mrow> <mo>−</mo> <mn>1</mn> </mrow> </msup> </semantics></math>) and by the M2 (blue dots: raw data, red dots: corrected data). The time axis is the local time.</p>
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<p>Scatter plots of wind speed between PV <span class="html-italic">Soya</span> and M2 (red: corrected, blue: raw) with linear regression lines. The values in parentheses are correlation coefficients.</p>
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<p>(<b>a</b>) Dual-mount of HWS, (<b>b</b>) assembly state of microcomputers and sensors, and (<b>c</b>) rose diagram of wind speed and direction during the hovering test by rotating 360<math display="inline"><semantics> <msup> <mrow/> <mo>∘</mo> </msup> </semantics></math> at 140-m AGL.</p>
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19 pages, 6438 KiB  
Article
Obstacle Avoidance-Based Autonomous Navigation of a Quadrotor System
by Mohammed A. Alanezi, Zaharuddeen Haruna, Yusuf A. Sha’aban, Houssem R. E. H. Bouchekara, Mouaaz Nahas and Mohammad S. Shahriar
Drones 2022, 6(10), 288; https://doi.org/10.3390/drones6100288 - 3 Oct 2022
Cited by 14 | Viewed by 5189
Abstract
Livestock management is an emerging area of application of the quadrotor, especially for monitoring, counting, detecting, recognizing, and tracking animals through image or video footage. The autonomous operation of the quadrotor requires the development of an obstacle avoidance scheme to avoid collisions. This [...] Read more.
Livestock management is an emerging area of application of the quadrotor, especially for monitoring, counting, detecting, recognizing, and tracking animals through image or video footage. The autonomous operation of the quadrotor requires the development of an obstacle avoidance scheme to avoid collisions. This research develops an obstacle avoidance-based autonomous navigation of a quadrotor suitable for outdoor applications in livestock management. A Simulink model of the UAV is developed to achieve this, and its transient and steady-state performances are measured. Two genetic algorithm-based PID controllers for the quadrotor altitude and attitude control were designed, and an obstacle avoidance algorithm was applied to ensure the autonomous navigation of the quadrotor. The simulation results show that the quadrotor flies to the desired altitude with a settling time of 6.51 s, an overshoot of 2.65%, and a steady-state error of 0.0011 m. At the same time, the attitude controller records a settling time of 0.43 s, an overshoot of 2.50%, and a zero steady-state error. The implementation of the obstacle avoidance scheme shows that the distance threshold of 1 m is sufficient for the autonomous navigation of the quadrotor. Hence, the developed method is suitable for managing livestock with the average size of an adult sheep. Full article
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<p>Steps in Algorithm Development for Quadrotor Autonomous Navigation Systems.</p>
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<p>Structure of Quadrotor [<a href="#B20-drones-06-00288" class="html-bibr">20</a>].</p>
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<p>Control Structure for the Navigation of the Quadrotor.</p>
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<p>Desired Roll and Pitch Rotations.</p>
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<p>Simulink Model of the Dynamic System.</p>
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<p>Altitude and Attitude Controller Design.</p>
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<p>GA-based Controller Tuning.</p>
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<p>Controller Testing on Navigation to a Goal Location.</p>
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<p>UAV Scenario Environment Without Obstacle (<b>Left</b>) and With Obstacle (<b>Right</b>).</p>
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<p>UAV 3D Animation.</p>
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<p>Model of the Obstacle Avoidance System.</p>
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<p>Response of the Quadrotor when Applying 5N Per Motor.</p>
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<p>Transient Response of the Quadrotor Control System; Altitude Control (<b>Top-Left</b>), Roll Control (<b>Top-Right</b>), Pitch Control (<b>Bottom-Left</b>), and Yaw Control (<b>Bottom-Right</b>).</p>
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<p>Quadrotor Navigation to a Goal Location of (10,10); x-y Trajectory (<b>Left</b>) and Altitude Response (<b>Right</b>).</p>
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<p>Quadrotor Navigation to a Goal Location of (50,50); x-y Trajectory (<b>Left</b>) and Altitude Response (<b>Right</b>).</p>
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<p>Control Action of the Quadrotor Obstacle Avoidance.</p>
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<p>Obstacle Avoidance at 0.5 m from the obstacle; 3D Motion of the Quadrotor (<b>Left</b>) and 2D Motion of the Quadrotor (<b>Right</b>).</p>
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<p>Obstacle Avoidance at 1 m from the obstacle; 3D Motion of the Quadrotor (<b>Left</b>) and 2D Motion of the Quadrotor (<b>Right</b>).</p>
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<p>Obstacle Avoidance Result with Three Obstacles; 3D Motion of the Quadrotor (<b>Left</b>) and 2D Motion of the Quadrotor (<b>Right</b>).</p>
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16 pages, 5490 KiB  
Article
Identification of INS Sensor Errors from Navigation Data Based on Improved Pigeon-Inspired Optimization
by Zhihua Li, Yimin Deng and Wenxue Liu
Drones 2022, 6(10), 287; https://doi.org/10.3390/drones6100287 - 2 Oct 2022
Cited by 5 | Viewed by 2132
Abstract
The error level of inertial sensor parameters determines the navigation accuracy of an inertial navigation system. For many applications, such as drones, errors in horizontal gyroscopes and accelerometers, can significantly affect the navigation results. Different from most methods of filter estimation, we innovatively [...] Read more.
The error level of inertial sensor parameters determines the navigation accuracy of an inertial navigation system. For many applications, such as drones, errors in horizontal gyroscopes and accelerometers, can significantly affect the navigation results. Different from most methods of filter estimation, we innovatively propose using evolutionary algorithms, such as the improved pigeon-inspired optimization (PIO) method, to identify sensor errors through navigation data. In this method, the navigation data are firstly collected; then, the improved carrier pigeon optimization method is used to find the optimal error parameter values of the horizontal gyroscope and accelerometer, so as to minimize the navigation result error calculated by the navigation data. At the same time, we propose a new improved method for pigeon-inspired optimization with dimension vectors adaptive mutation (DVPIO for short) that can avoid local optima in the later stages of the iteration. In the DVPIO method, 2n particles with poor fitness are selected for the following variation, with 2n dimension vectors when it is judged that the position is premature, where n represents the number of parameters to be identified; a dimension vector only represents the positive or negative change of a parameter, whose change amount is d can be adjusted adaptively. DVPIO method has better stability, faster convergence speed, and higher accuracy. This work has potential to reduce the need for the disassembly and assembly of the INS and return it to the manufacturer for calibration. Full article
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<p>Optical INS.</p>
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<p>Identification of INS sensor errors from navigation data based on DVPIO.</p>
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<p>Velocity error when <math display="inline"><semantics> <mrow> <msub> <mrow> <mrow> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi>and</mi> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Velocity error when <math display="inline"><semantics> <mrow> <msub> <mrow> <mrow> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mo>−</mo> <mn>2</mn> <msub> <mi mathvariant="sans-serif">σ</mi> <mi mathvariant="normal">A</mi> </msub> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi>and</mi> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Velocity error when <math display="inline"><semantics> <mrow> <msub> <mrow> <mrow> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi>and</mi> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>1.5</mn> <msub> <mi mathvariant="sans-serif">σ</mi> <mi mathvariant="normal">A</mi> </msub> </mrow> </semantics></math>.</p>
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<p>Velocity error when <math display="inline"><semantics> <mrow> <msub> <mrow> <mrow> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>2</mn> <msub> <mi mathvariant="sans-serif">σ</mi> <mi mathvariant="normal">D</mi> </msub> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi>and</mi> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Velocity error when <math display="inline"><semantics> <mrow> <msub> <mrow> <mrow> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mo>−</mo> <mn>1.5</mn> <msub> <mi mathvariant="sans-serif">σ</mi> <mi mathvariant="normal">D</mi> </msub> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi>and</mi> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>0</mn> </mrow> </semantics></math>.</p>
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<p>Velocity error when <math display="inline"><semantics> <mrow> <msub> <mrow> <mrow> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mn>2</mn> <msub> <mi mathvariant="sans-serif">σ</mi> <mi mathvariant="normal">D</mi> </msub> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">D</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mo>−</mo> <mn>1.5</mn> <msub> <mi mathvariant="sans-serif">σ</mi> <mi mathvariant="normal">D</mi> </msub> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">x</mi> </mrow> </msub> <mo>=</mo> <mo>−</mo> <mn>2</mn> <msub> <mi mathvariant="sans-serif">σ</mi> <mi mathvariant="normal">A</mi> </msub> <mo>,</mo> <msub> <mrow> <mrow> <mtext> </mtext> <mi>and</mi> <mtext> </mtext> <mi mathvariant="sans-serif">δ</mi> <mi mathvariant="normal">A</mi> </mrow> </mrow> <mrow> <mn>0</mn> <mi mathvariant="normal">y</mi> </mrow> </msub> <mo>=</mo> <mn>1.5</mn> <msub> <mi mathvariant="sans-serif">σ</mi> <mi mathvariant="normal">A</mi> </msub> </mrow> </semantics></math>.</p>
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<p>Fitness comparison of GA, PSO, PIO, and DVPIO (3 calculations for each method).</p>
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<p>PIO particle swarm location distribution in each dimension(Different colors of lines represent different dimensions).</p>
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<p>PIO particle swarm global optimal location.</p>
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<p>DVPIO particle swarm location distribution in each dimension(Different colors of lines represent different dimensions).</p>
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<p>DVPIO particle swarm global optimal location.</p>
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16 pages, 2167 KiB  
Article
Flying Washer: Development of High-Pressure Washing Aerial Robot Employing Multirotor Platform with Add-On Thrusters
by Ryo Miyazaki, Hannibal Paul, Takamasa Kominami, Ricardo Rosales Martinez and Kazuhiro Shimonomura
Drones 2022, 6(10), 286; https://doi.org/10.3390/drones6100286 - 2 Oct 2022
Cited by 5 | Viewed by 4364
Abstract
In this study, we propose a multirotor aerial robot for high-pressure washing tasks at high altitudes. The aerial robot consists of a multirotor platform, an add-on planar translational driving system (ATD), a visual sensing system, and a high-pressure washing system. The ATD consists [...] Read more.
In this study, we propose a multirotor aerial robot for high-pressure washing tasks at high altitudes. The aerial robot consists of a multirotor platform, an add-on planar translational driving system (ATD), a visual sensing system, and a high-pressure washing system. The ATD consists of three ducted fans, which can generate force in all directions on the horizontal plane. The ATD also allows the multirotor to suppress the reaction force generated by the nozzle of a high-pressure washing system and inject water accurately. In this study, we propose a method to precisely inject water by installing an ATD in the multirotor and using its driving force to suppress the reaction force and move the multirotor while keeping its posture horizontal. The semi-autonomous system was designed to allow the operator to maneuver the multirotor while maintaining a constant distance from the wall by the sensor feedback with onboard LiDAR or stereo camera. In the experiment, we succeeded in performing the high-pressure washing task in a real environment and verified that the reaction force generated from the nozzle was actually suppressed during the task. Full article
(This article belongs to the Special Issue Applications of UAVs in Civil Infrastructure)
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<p>Add-on planar translational driving system (ATD) with the multirotor for high-place, high-pressure washing tasks.</p>
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<p>Concept of multirotor-based high-pressure washing. (<b>A</b>) An additional force is needed to maintain UAV position while water injection. (<b>B</b>) Generating thrust in any horizontal direction is required while maintaining the attitude of the aircraft horizontally. In this work, ATD provides this function.</p>
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<p>(<b>A</b>) Experimental setup of force measurement while injecting the water. (<b>B</b>) Experimental results of the force generated by water injection. (<b>C</b>) Experimental results of the washing power at each distance.</p>
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<p>(<b>A</b>) Overview of the ATD and its defined parameters. (<b>B</b>) Implementation of the ATD. (<b>C</b>) Model of the ATD. (<b>D</b>) Experimental result of the output force of the ATD for different input thrusts. The linear approximation is <math display="inline"><semantics> <mrow> <mi>y</mi> <mo>=</mo> <mn>0.1319</mn> <mi>x</mi> <mo>−</mo> <mn>0.0706</mn> </mrow> </semantics></math>.</p>
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<p>Pictures of aerial robot system of multirotor with ATD for high-pressure washing.</p>
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<p>Block diagram of the aerial robot system of multirotor with ATD.</p>
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<p>(<b>A</b>) Sensing result of the LiDAR. From the fitted line (green line), it shows the estimation results of the angle and the distance to the wall in front of the UAV. (<b>B</b>) The case of an obstacle in the ‘warning region’ (2 m × 1 m). (<b>C</b>) The case of an obstacle in the ‘critical region’ (1 m × 1 m).</p>
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<p>Experimental setup of flying test while maintaining a constant distance from the wall using sensor feedback.</p>
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<p>(<b>A</b>) Experimental results when using LiDAR feedback. (<b>B</b>) Experimental results when using camera feedback.</p>
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<p>(<b>A</b>) Continuous image of high-pressure water injection while flying in the ATD control mode. (<b>B</b>) Movement trajectory of the multirotor during water jetting. The coordinates of the start and end represent (px,py,pz), and blue arrows at each measurement point indicate the direction of the UAV’s water jet.</p>
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<p>(<b>A</b>) Experimental results of a time series graph of the movement trajectory shown in <a href="#drones-06-00286-f010" class="html-fig">Figure 10</a>. (<b>B</b>) Experimental results of velocity changes during the water jet. (<b>C</b>) Experimental results of attitude changes during the water jet.</p>
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<p>(<b>A</b>) Continuous images of washing tasks during flight. (<b>B</b>) Movement trajectory of the multirotor during the washing task. The coordinates of the start and end represent (px, py, pz), and red arrows at each measurement point indicate the direction of the UAV’s water jet.</p>
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<p>(<b>A</b>) Experimental results of a time series graph of the movement trajectory shown in <a href="#drones-06-00286-f012" class="html-fig">Figure 12</a>. (<b>B</b>) Experimental results of velocity changes during the washing task. (<b>C</b>) Experimental results of attitude changes during the washing task.</p>
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<p>Pictures of the multirotor flying to maximum washable height. The height was about 12 m.</p>
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27 pages, 12486 KiB  
Article
Minimal Surfaces as an Innovative Solution for the Design of an Additive Manufactured Solar-Powered Unmanned Aerial Vehicle (UAV)
by César García-Gascón, Pablo Castelló-Pedrero and Juan Antonio García-Manrique
Drones 2022, 6(10), 285; https://doi.org/10.3390/drones6100285 - 2 Oct 2022
Cited by 8 | Viewed by 3846
Abstract
This paper aims to describe the methodology used in the design and manufacture of a fixed-wing aircraft manufactured using additive techniques together with the implementation of technology based on solar panels. The main objective is increasing the autonomy and range of the UAV’s [...] Read more.
This paper aims to describe the methodology used in the design and manufacture of a fixed-wing aircraft manufactured using additive techniques together with the implementation of technology based on solar panels. The main objective is increasing the autonomy and range of the UAV’s autonomous missions. Moreover, one of the main targets is to improve the capabilities of the aeronautical industry towards sustainable aircrafts and to acquire better mechanical properties owing to the use of additive technologies and new printing materials. Further, a lower environmental impact could be achieved through the use of renewable energies. Material extrusion (MEX) technology may be able to be used for the manufacture of stronger and lighter parts by using gyroids as the filling of the printed material. The paper proposes the use of minimal surfaces for the reinforcement of the UAV aircraft wings. This type of surface was never used because it is not possible to manufacture it using conventional techniques. The rapid growth of additive technologies led to many expectations for new design methodologies in the aeronautical industry. In this study, mechanical tests were carried out on specimens manufactured with different geometries to address the design and manufacture of a UAV as a demonstrator. In addition, to carry out the manufacture of the prototype, a 3D printer with a movable bench similar to a belt, that allows for the manufacture of parts without limitations in the Z axis, was tested. The parts manufactured with this technique can be structurally improved, and it is possible to avoid manufacturing multiple prints of small parts of the aircraft that will have to be glued later, decreasing the mechanical properties of the UAV. The conceptual design and manufacturing of a solar aircraft, SolarÍO, using additive technologies, is presented. A study of the most innovative 3D printers was carried out that allowed for the manufacture of parts with an infinite Z-axis and, in addition, a filler based on minimal surfaces (gyroids) was applied, which considerably increased the mechanical properties of the printed parts. Finally, it can be stated that in this article, the potential of the additive manufacturing as a new manufacturing process for small aircrafts and for the aeronautical sector in the future when new materials and more efficient additive manufacturing processes are already developed is demonstrated. Full article
(This article belongs to the Special Issue Conceptual Design, Modeling, and Control Strategies of Drones-II)
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Graphical abstract

Graphical abstract
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<p>Timeline invention of different 3D printing technologies.</p>
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<p>Cost per unit vs quantity and complexity for traditional and additive manufacturing techniques.</p>
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<p>Energy balance of solar UAV.</p>
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<p>Soap films and minimal surfaces.</p>
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<p>Gyroid surface. (<b>a</b>) Repeated unit cell. (<b>b</b>) Unit cell.</p>
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<p>Specimens set to be printed (<b>a</b>) and printed (<b>b</b>).</p>
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<p>The Blackbelt 3D printer and the specimens printed.</p>
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<p>Specimen with gyroid in X direction (<b>a</b>). Specimen with gyroid in Y direction (<b>b</b>).</p>
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<p>3D printed specimens with gyroid in both directions - X direction (<b>a</b>) and Y direction (<b>b</b>) and inserted CFRP rods with a diameter of 1.5 mm and length of 150 mm. Dimensions (mm) of the CFRP rods locations are shown.</p>
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<p>Specimens with different printing angles (θp): 15°, 25°, and 45°.</p>
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<p>Experiment setup with specimen in position, ready to be tested.</p>
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<p>Evolution of the bend extension of the specimen printed with an angle of 0°and infill density of 9.5% with an applied load.</p>
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<p>Evolution of the bend extension of the specimen printed with an angle of 90° and infill density of 13% with an applied load.</p>
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<p>Specimen reinforced with CFRP, angle of 90°, and infill density of 13%.</p>
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<p>Evolution of the bend extension of the specimen printed with an angle of 90° and infill density of 15% with an applied load, depending on the gyroid direction.</p>
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<p>Evolution of the bend deformation of the specimen, printed at different degrees, with an applied load.</p>
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<p>Compression test setup with specimen between plates.</p>
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<p>Comparison of the evolution of the displacement of the specimen with a force applied for different infill densities.</p>
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<p>Comparison of the evolution of the displacement of the specimen with a force applied for different thicknesses.</p>
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<p>UAV solar plane, SolarÍO (1/2).</p>
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<p>UAV solar plane, SolarÍO (2/2).</p>
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<p>Wing finite element mesh and applied loads (<b>a</b>). Wing displacement and von Mises stress; mm and MPa (<b>b</b>).</p>
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<p>Wing finite element mesh and applied loads (<b>a</b>). Wing displacement and von Mises stress; mm and MPa (<b>b</b>).</p>
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<p>Solar panel specifications.</p>
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<p>Distribution of the solar panels along the wing of the SolarÍO.</p>
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<p>Connecting the MPPT to the SolarÍO circuit.</p>
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<p>Side view of the simplified situation of the error that occurred. Red lines represent the filaments.</p>
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<p>Visualization of the wing in Blackbelt Cura.</p>
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<p>Cross-section of the wing in Blackbelt Cura.</p>
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<p>Fuselage set to be printed (<b>left</b>) and printed (<b>right</b>) with the Blackbelt printer.</p>
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<p>Wing printed on Blackbelt 3D printer.</p>
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<p>Four parts of the wing on the conventional 3D printer.</p>
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20 pages, 3242 KiB  
Review
Comprehensive Review of UAV Detection, Security, and Communication Advancements to Prevent Threats
by Ghulam E. Mustafa Abro, Saiful Azrin B. M. Zulkifli, Rana Javed Masood, Vijanth Sagayan Asirvadam and Anis Laouiti
Drones 2022, 6(10), 284; https://doi.org/10.3390/drones6100284 - 1 Oct 2022
Cited by 74 | Viewed by 16979
Abstract
It has been observed that unmanned aerial vehicles (UAVs), also known as drones, have been used in a very different way over time. The advancements in key UAV areas include detection (including radio frequency and radar), classification (including micro, mini, close range, short [...] Read more.
It has been observed that unmanned aerial vehicles (UAVs), also known as drones, have been used in a very different way over time. The advancements in key UAV areas include detection (including radio frequency and radar), classification (including micro, mini, close range, short range, medium range, medium-range endurance, low-altitude deep penetration, low-altitude long endurance, and medium-altitude long endurance), tracking (including lateral tracking, vertical tracking, moving aerial pan with moving target, and moving aerial tilt with moving target), and so forth. Even with all of these improvements and advantages, security and privacy can still be ensured by researching a number of key aspects of an unmanned aerial vehicle, such as through the jamming of the control signals of a UAV and redirecting them for any high-assault activity. This review article will examine the privacy issues related to drone standards and regulations. The manuscript will also provide a comprehensive answer to these limitations. In addition to updated information on current legislation and the many classes that can be used to establish communication between a ground control room and an unmanned aerial vehicle, this article provides a basic overview of unmanned aerial vehicles. After reading this review, readers will understand the shortcomings, the most recent advancements, and the strategies for addressing security issues, assaults, and limitations. The open research areas described in this manuscript can be utilized to create novel methods for strengthening the security and privacy of an unmanned aerial vehicle. Full article
(This article belongs to the Special Issue Advances in UAV Detection, Classification and Tracking)
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<p>Security and privacy threats of UAVs.</p>
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<p>Communication channels mostly used to control UAVs.</p>
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<p>Classification of UAVs in terms of altitude.</p>
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<p>Components of an unmanned aerial vehicle.</p>
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<p>Communication methods for high- and low-altitude levels.</p>
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<p>Utilization of drones in several domains.</p>
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<p>Malevolent and benevolent usages of a drone.</p>
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<p>UAVs with open propellers.</p>
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<p>UAVs with closed and safety propellers.</p>
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<p>UAV attack vector with reported incidents.</p>
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26 pages, 4053 KiB  
Article
DEDG: Cluster-Based Delay and Energy-Aware Data Gathering in 3D-UWSN with Optimal Movement of Multi-AUV
by Reem Alkanhel, Amir Chaaf, Nagwan Abdel Samee, Manal Abdullah Alohali, Mohammed Saleh Ali Muthanna, Dmitry Poluektov and Ammar Muthanna
Drones 2022, 6(10), 283; https://doi.org/10.3390/drones6100283 - 1 Oct 2022
Cited by 11 | Viewed by 2695
Abstract
The monitoring of underwater aquatic habitats and pipeline leakages and disaster prevention are assisted by the construction of an underwater wireless sensor network (UWSN). The deployment of underwater sensors consumes energy and causes delay when transferring the gathered sensed data via multiple hops. [...] Read more.
The monitoring of underwater aquatic habitats and pipeline leakages and disaster prevention are assisted by the construction of an underwater wireless sensor network (UWSN). The deployment of underwater sensors consumes energy and causes delay when transferring the gathered sensed data via multiple hops. The consumption of energy and delays are minimized by means of an autonomous unmanned vehicle (AUV). This work addresses the idea of reducing energy and delay by incorporating an AUVs-assisted, three-dimensional UWSN (3D-UWSN) called DEDG 3D-UWSN. Energy in the sensor nodes is saved by clustering and scheduling; on the other hand, the delay is minimized by the movement of the AUV and inter-cluster routing. In clustering, multi-objective spotted hyena optimization (MO-SHO) is applied for the selection of the best sensor for the cluster head, which is responsible for assigning sleep schedules for members. According to the total number of members, an equal half of the members is provided with sleep slots based on the energy and hop counts. The redundancy in the gathered data is eliminated by measuring the Hassanat distance. Then, the moving AUV is able to predict its movement by the di-factor actor–critic path prediction method. The mid-point among the four heads is determined so that the AUV can collect data from four heads at a time. In cases where the waiting time of the CH is exceeded, three-step, inter-cluster routing is executed. The three steps are the discovery of possible routes, ignoring the longest paths and validating the filtered path with a fuzzy–LeNet method. In this 3D-UWSN, the sensed data are not always normal, and, hence, a weighted method is presented to transfer emergency events by selecting forwarders. This work is implemented on Network Simulator version 3.26 to test the results. It achieves better efficiency in terms of data collection delay, end-to-end delay, AUV tour length, network lifetime, number of alive nodes and energy consumption. Full article
(This article belongs to the Special Issue Drone Computing Enabling IoE)
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<p>DEDG 3D-UWSN architecture.</p>
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<p>Three-step, inter-Cluster routing with route validation in fuzzy–LeNet.</p>
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<p>Movement of AUV in 3D-UWSN.</p>
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<p>Simulation workflow of DEDG 3D-UWSN.</p>
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<p>Ns3 Setup for DEDG 3D-UWSN.</p>
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<p>Application scenario.</p>
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<p>Comparison of energy consumption.</p>
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<p>Comparison of alive nodes.</p>
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<p>Comparison of network lifetime.</p>
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<p>Comparison of packet delivery ratios.</p>
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<p>Comparison of end-to-end delay.</p>
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<p>Comparison of collection delay.</p>
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33 pages, 4021 KiB  
Article
Routing in Solar-Powered UAV Delivery System
by Zijing Tian, Zygmunt J. Haas and Shatavari Shinde
Drones 2022, 6(10), 282; https://doi.org/10.3390/drones6100282 - 30 Sep 2022
Cited by 13 | Viewed by 2837
Abstract
As interest grows in unmanned aerial vehicle (UAV) systems, UAVs have been proposed to take on increasingly more tasks that were previously assigned to humans. One such task is the delivery of goods within urban cities using UAVs, which would otherwise be delivered [...] Read more.
As interest grows in unmanned aerial vehicle (UAV) systems, UAVs have been proposed to take on increasingly more tasks that were previously assigned to humans. One such task is the delivery of goods within urban cities using UAVs, which would otherwise be delivered by terrestrial means. However, the limited endurance of UAVs due to limited onboard energy storage makes it challenging to practically employ UAV technology for deliveries across long routes. Furthermore, the relatively high cost of building UAV charging stations prevents the dense deployment of charging facilities. Solar-powered UAVs can ease this problem, as they do not require charging stations and can harvest solar power in the daytime. This paper introduces a solar-powered UAV goods delivery system to plan delivery missions with solar-powered UAVs (SPUs). In this study, when the SPUs run out of power, they charge themselves on landing places provided by customers instead of charging stations. Some advanced path planning algorithms are proposed to minimize the overall mission time in the statically charging efficiency environment. We further consider routing in the dynamically charging efficiency environment and propose some mission arrangement protocols to manage different missions in the system. The simulation results demonstrate that the algorithms proposed in our work perform significantly better than existing UAV path planning algorithms in solar-powered UAV systems. Full article
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<p>Example of a single SPU problem.</p>
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<p>Reachable nodes of a node in the local city map.</p>
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<p>S. Kaplanis’s charging efficiency prediction from [<a href="#B5-drones-06-00282" class="html-bibr">5</a>].</p>
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<p>City map with landing places (nodes) and stores.</p>
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<p>An example of a ten-node local city map.</p>
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<p>The GOA algorithm with pruning strategy.</p>
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<p>Path <math display="inline"><semantics> <mrow> <msub> <mi mathvariant="normal">P</mi> <mi mathvariant="normal">k</mi> </msub> </mrow> </semantics></math>, which contains nodes <math display="inline"><semantics> <mrow> <mrow> <mo>[</mo> <mrow> <msub> <mi mathvariant="normal">v</mi> <mi mathvariant="normal">S</mi> </msub> <mo>,</mo> <msub> <mi mathvariant="normal">v</mi> <mrow> <msub> <mi mathvariant="normal">k</mi> <mn>1</mn> </msub> </mrow> </msub> <mo>,</mo> <msub> <mi mathvariant="normal">v</mi> <mrow> <msub> <mi mathvariant="normal">k</mi> <mn>2</mn> </msub> </mrow> </msub> <mo>…</mo> <msub> <mrow> <mrow> <mo> </mo> <mi mathvariant="normal">v</mi> </mrow> </mrow> <mrow> <msub> <mi mathvariant="normal">k</mi> <mi mathvariant="normal">j</mi> </msub> </mrow> </msub> <mo>,</mo> <msub> <mrow> <mrow> <mo> </mo> <mi mathvariant="normal">v</mi> </mrow> </mrow> <mi mathvariant="normal">D</mi> </msub> </mrow> <mo>]</mo> </mrow> </mrow> </semantics></math>.</p>
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<p>Example when <math display="inline"><semantics> <mrow> <msub> <mi mathvariant="sans-serif">ρ</mi> <mi mathvariant="normal">i</mi> </msub> <mo>&gt;</mo> <msub> <mi mathvariant="sans-serif">ρ</mi> <mrow> <mi mathvariant="normal">i</mi> <mo>+</mo> <mn>1</mn> </mrow> </msub> </mrow> </semantics></math>, <math display="inline"><semantics> <mrow> <msub> <mi mathvariant="normal">x</mi> <mn>2</mn> </msub> <mo>&lt;</mo> <mn>360</mn> </mrow> </semantics></math> and <math display="inline"><semantics> <mrow> <msub> <mi mathvariant="normal">x</mi> <mn>3</mn> </msub> <mo>&lt;</mo> <mn>360</mn> </mrow> </semantics></math> (<math display="inline"><semantics> <mrow> <msub> <mi mathvariant="sans-serif">ρ</mi> <mi mathvariant="normal">i</mi> </msub> <mo>=</mo> <mn>1</mn> <mo>,</mo> <msub> <mrow> <mrow> <mo> </mo> <mi mathvariant="sans-serif">ρ</mi> </mrow> </mrow> <mrow> <mi mathvariant="normal">i</mi> <mo>+</mo> <mn>1</mn> </mrow> </msub> <mo>=</mo> <mn>0.75</mn> <mo>,</mo> <msub> <mrow> <mrow> <mo> </mo> <mi mathvariant="normal">F</mi> </mrow> </mrow> <mrow> <mi mathvariant="normal">i</mi> <mo>+</mo> <mn>1</mn> </mrow> </msub> <mo>=</mo> <mn>23</mn> </mrow> </semantics></math>).</p>
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<p>Charging time assignment example using Algorithm 1.</p>
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<p>(<b>a</b>–<b>c</b>) Maximum improvement by the GOA, where the number of nodes were 40, 60, and 80 (in <a href="#drones-06-00282-f010" class="html-fig">Figure 10</a>, max. improvement represents the maximum improvement an algorithm could achieve, and min. charging efficiency represents the minimum possible charging efficiency in the city map).</p>
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<p>(<b>a</b>–<b>c</b>) Maximum improvement by the GOA, where the number of nodes were 40, 60, and 80 (in <a href="#drones-06-00282-f010" class="html-fig">Figure 10</a>, max. improvement represents the maximum improvement an algorithm could achieve, and min. charging efficiency represents the minimum possible charging efficiency in the city map).</p>
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<p>Ratio of time (unpruned GOA: pruned GOA).</p>
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<p>(<b>a</b>–<b>c</b>) Maximum improvements by Algorithms 3 and 4, where the number of nodes were 40, 60, and 80 (in <a href="#drones-06-00282-f012" class="html-fig">Figure 12</a>, DG-CTA represents Algorithm 3, and heuristic represents Algorithm 4; CTA represents Algorithm 1, and Dij represents the scheme where UAVs always charged themselves to a full battery state on each passed node).</p>
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