Artigos de revistas: "Fixed-wing unmanned aerial vehicle"

1

Zou, Jie-Tong, e Pan Zheng-Yan. "THE DEVELOPMENT OF TILT-ROTOR UNMANNED AERIAL VEHICLE". Transactions of the Canadian Society for Mechanical Engineering 40, n.º 5 (dezembro de 2016): 909–21. http://dx.doi.org/10.1139/tcsme-2016-0075.

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In this research, we had developed quad-rotor unmanned aerial vehicles with the tilt-rotor mechanism. People are eager to fly therefore the development of aerial vehicles, such as fixed-wing aerial vehicles and multi-rotor aerial vehicles, has grown rapidly in recent years. The multi-rotor vertical take-off and landing (VTOL) unmanned aerial vehicle which can fly stably and hover in a fix position developed the fastest. Comparing the general fixed-wing aircrafts and rotorcrafts, fixed-wing aircrafts can fly with a higher speed than rotorcrafts, but they do not have the VTOL and hovering abilities. The proposed quad-rotor aerial vehicle with tilt-rotor mechanism has two flight modes: rotorcraft and fixed-wing aircraft flight mode. It can take-off and land vertically in rotorcraft mode and can also fly faster in fixed-wing aircraft flight mode. The dynamic equations of the proposed quad-rotor aerial vehicle with tiltrotor mechanism are also studied in this paper.

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Oktay, Tugrul, Harun Celik e Ilke Turkmen. "Maximizing autonomous performance of fixed-wing unmanned aerial vehicle to reduce motion blur in taken images". Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 232, n.º 7 (28 de março de 2018): 857–68. http://dx.doi.org/10.1177/0959651818765027.

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In this study, reducing motion blur in images taken by our unmanned aerial vehicle is investigated. Since shakes of unmanned aerial vehicle cause motion blur in taken images, autonomous performance of our unmanned aerial vehicle is maximized to prevent it from shakes. In order to maximize autonomous performance of unmanned aerial vehicle (i.e. to reduce motion blur), initially, camera mounted unmanned aerial vehicle dynamics are obtained. Then, optimum location of unmanned aerial vehicle camera is estimated by considering unmanned aerial vehicle dynamics and autopilot parameters. After improving unmanned aerial vehicle by optimum camera location, dynamics and controller parameters, it is called as improved autonomous controlled unmanned aerial vehicle. Also, unmanned aerial vehicle with camera fixed at the closest point to center of gravity is called as standard autonomous controlled unmanned aerial vehicle. Both improved autonomous controlled and standard autonomous controlled unmanned aerial vehicles are performed in real time flights, and approximately same trajectories are tracked. In order to compare performance of improved autonomous controlled and standard autonomous controlled unmanned aerial vehicles in reducing motion blur, a motion blur kernel model which is derived using recorded roll, pitch and yaw angles of unmanned aerial vehicle is improved. Finally, taken images are simulated to examine effect of unmanned aerial vehicle shakes. In comparison with standard autonomous controlled flight, important improvements on reducing motion blur are demonstrated by improved autonomous controlled unmanned aerial vehicle.

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3

Zhang, Xiangyin, e Haibin Duan. "Altitude consensus based 3D flocking control for fixed-wing unmanned aerial vehicle swarm trajectory tracking". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 230, n.º 14 (6 de agosto de 2016): 2628–38. http://dx.doi.org/10.1177/0954410016629692.

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This paper studies the 3D flocking control problem for unmanned aerial vehicle swarm when tracking a desired trajectory. In order to allow the unmanned aerial vehicle swarm to form the stable flocking geometry on a same horizontal plane, the altitude consensus algorithm is applied to the unmanned aerial vehicle altitude control channel, using the trajectory altitude as the external input signals. The flocking control algorithm is only performed in the horizontal channel to control the horizontal position of unmanned aerial vehicles. The distributed tracking algorithm, which controls the local averages of position and velocity of each unmanned aerial vehicle, is implemented to achieve the better tracking performance. The improved artificial potential field method is introduced to achieve the smooth trajectory when avoiding obstacles. The practical dynamic and constraints of unmanned aerial vehicles are also taken into account. Numerical simulations are performed to test the performance of the proposed control algorithm.

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Eftekhari, Shahrooz, e Abdulkareem Sh Mahdi Al-Obaidi. "Investigation of a Cruising Fixed Wing Mini Unmanned Aerial Vehicle Performance Optimization". Indonesian Journal of Science and Technology 4, n.º 2 (9 de julho de 2019): 280–93. http://dx.doi.org/10.17509/ijost.v4i2.18185.

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The applications of unmanned aerial vehicles have been extended through the recent decades and they are utilized for both civil and military applications. The urge to utilize unmanned aerial vehicles for civil purposes has elevated researchers and industries interest towards the mini unmanned aerial vehicle (MUAV) category due to its suitable configurations and capabilities for multidisciplinary civil purposes. This study is an effort to further enhance the aerodynamic efficiency of MUAVs through a parametric study of the wing and proposing an innovative bioinspired wing design. The research is conducted utilizing numerical simulation and experimental validation. This research provides a better understanding of different wing parameter(s) effect on the aerodynamic performance of the wing and mini unmanned aerial vehicles. A new wing configuration is designed, implemented and evaluated. The wing is named as Alpine since it is inspired by biomimicry of alpine swift bird. Evaluation of the new wing geometry shows that the Alpine wing geometry performs 35.9% more efficient compared to an existing wing with similar wing area. Hence, the aerodynamic efficiency optimization is achieved for the Alpine wing which helps to enhance the performance of MUAVs.

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Nasab, Hamed Mortazavi, e Naser Navazani. "Adaptive Control for Trajectory Tracking of an Unmanned Aerial Vehicle". Advanced Engineering Forum 17 (junho de 2016): 101–10. http://dx.doi.org/10.4028/www.scientific.net/aef.17.101.

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In this paper, an unmanned aerial vehicle (UAV) with fixed-wing in normal condition flight, and fixed height, is considered and along with this process, kinematics model of UAV, assumed to have parametric uncertainty. In this situation the target of designing of proper controller family, based on switching logic, is to control the speed and roll angle of fixed-wing unmanned aerial vehicle in order to track desired path with minimum error. The desired path will be generated by trajectory maker block. The results of simulation on a fixed-wing UAV are presented to show the efficiency of the method.

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6

Suroso, Indreswari, e Erwhin Irmawan. "Analysis Of Aerial Photography With Drone Type Fixed Wing In Kotabaru, Lampung". Journal of Applied Geospatial Information 2, n.º 1 (4 de maio de 2018): 102–7. http://dx.doi.org/10.30871/jagi.v2i1.738.

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In the world of photography is very closely related to the unmanned aerial vehicle called drones. Drones mounted camera so that the plane is pilot controlled from the mainland. Photography results were seen by the pilot after the drone aircraft landed. Drones are unmanned drones that are controlled remotely. Unmanned Aerial Vehicle (UAV), is a flying machine that operates with remote control by the pilot. Methode for this research are preparation assembly of drone, planning altitude flying, testing on ground, camera of calibration, air capture, result of aerial photos and analysis of result aerial photos. There are two types of drones, multicopter and fixed wing. Fixed wing has an airplane like shape with a wing system. Fixed wing use bettery 4000 mAh . Fixed wing drone in this research used mapping in This drone has a load ability of 1 kg and operational time is used approximately 30 minutes for an areas 20 to 50 hectares with a height of 100 m to 200 m and payload 1 kg above ground level. The aerial photographs in Kotabaru produce excellent aerial photographs that can help mapping the local government in the Kotabaru region.

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7

Yang, Mingxiao, Sifan Wang, Kai Hu e Tongyan Liu. "Wing Optimization Design Based on Composite Global Hawk Unmanned Aerial Vehicle". Journal of Physics: Conference Series 2557, n.º 1 (1 de julho de 2023): 012087. http://dx.doi.org/10.1088/1742-6596/2557/1/012087.

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Abstract Composite materials have become the approach to solve the high stiffness and light weight of unmanned aerial vehicle structures. The wing had an extremely important influence on the flight of the unmanned aerial vehicle. The optimal composite wing design aroused widespread attention since it enhanced the aerodynamic performance of unmanned aerial vehicles. This article was intended to optimize and design the unmanned aerial vehicle with advantages in aerodynamic performance. According to the parameters of the military-civilian integrated unmanned aerial vehicle, a three-dimensional model of the overall structure of the composite Global Hawk unmanned aerial vehicle was designed. The effect of composite materials on the wing and the optimization of the laminate layup structure were studied. XFLR5 software was utilized to analyze the aerodynamic performance of the wing. The original NACA0012 airfoil and the optimized NACA3412 airfoil of the composite Global Hawk unmanned aerial vehicle were analyzed respectively for structure and performance. XFLR5 software was utilized to conduct flight simulation under the set parameters, and the effect of changing the angle of attack on the wing performance was analyzed. The results demonstrated that the optimized wing outperformed the original wing in terms of the lift, drag, torque, and lift-drag ratio.

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Krishnakumar, R., K. Senthil Kumar e T. Anand. "Design and Development of Vertical Takeoff and Horizontal Transition Mini Unmanned Aerial Vehicle". Advanced Materials Research 1016 (agosto de 2014): 436–40. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.436.

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In recent years Unmanned Aerial Vehicles (UAV) has become a significant segment of the aviation industry. They can be chosen to be designed as fixed wing or Rotary wing type. Fixed-wing aircraft has the performance of fast forward movement, long range and superior endurance due to its gliding capabilities with no power. Unlike the fixed wing models, rotary wing mini-copters are able to fly in all directions, hover in a fixed position with minimal space for takeoff and landing. This makes them the perfect instrument for detailed inspection work or surveying. Implementing a hybrid UAV has the advantages of both fixed-wing and rotary wing UAV. This paper aims to brief on the design, development and testing of a hybrid tilt body UAV with four rotors. The hybrid vehicle comprises two units, an aerial unit and a ground unit. The aerial unit consists of an unmanned aircraft system. The ground unit consists of means to view and post-data processing of video/image sent by the UAV if it is used for aerial surveillance and control, navigate and guide the aircraft. To proceed, a novel hybrid UAV with capability of Vertical Take Off and Landing (VTOL) and horizontal flight is developed and its response during the transition from VTOL to horizontal flight is analyzed.

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9

Challa, Vinay Reddy, e Ashwini Ratnoo. "On Maneuverability of Fixed-Wing Unmanned Aerial Vehicle Formations". Journal of Guidance, Control, and Dynamics 44, n.º 7 (julho de 2021): 1327–44. http://dx.doi.org/10.2514/1.g005409.

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10

Zhai, Rui Yong, Wen Dong Zhang, Zhao Ying Zhou, Sheng Bo Sang e Pei Wei Li. "Trajectory Tracking Control for Micro Unmanned Aerial Vehicles". Advanced Materials Research 798-799 (setembro de 2013): 448–51. http://dx.doi.org/10.4028/www.scientific.net/amr.798-799.448.

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This article considers the problem of trajectory tracking control for a micro fixed-wing unmanned air vehicle (UAV). With Bank-to-Turn (BTT) method to manage lateral deviation control of UAV, this paper discusses the outer loop guidance system, which separates the vehicle guidance problems into lateral control loop and longitudinal control loop. Based on the kinematic model of the coordinated turning of UAV, the aircraft can track a pre-specified flight path with desired error range. Flight test results on a fixed-wing UAV have indicated that the trajectory tracking control law is quite effective.

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11

Kaviyarasu, A., A. Saravanakumar e M. Logavenkatesh. "Software in Loop Simulation based Waypoint Navigation for Fixed Wing UAV". Defence Science Journal 71, n.º 4 (1 de julho de 2021): 448–55. http://dx.doi.org/10.14429/dsj.71.16164.

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Software in loop simulation (SILS) based waypoint navigation test platform being presented in this paper for fixed wing unmanned aerial vehicle. The proposed platform helps to test waypoint navigation algorithm before implementing into real time environment. Matlab/Simulink and X-plane flight simulator are chosen for the proposed platform. The interface between these two platforms are done by using user datagram protocol (UDP). The waypoint navigation which is to be tested is run in Matlab/Simulink environment where as fixed wing model runs in X-plane simulator. Inverted T tail fixed wing unmanned aerial vehicle configuration is chosen for this research work to verify both its inner loop (attitude control) and outer loop (navigation control). Navigation algorithm executed in Matlab/Simulink compares difference between current and desired latitude longitude position to command flight simulator to reach its desired waypoint. Navigation towards a desired waypoint will be achieved by varying inner loop attitude command of an unmanned aerial vehicle. Finally results are observed and performances are verified in X-plane simulator.

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12

Zhang, Jialong, Bing Xiao, Maolong Lv e Qiang Zhang. "Design and flight-stability analysis of a closed fixed-wing unmanned aerial vehicle formation controller". Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 233, n.º 8 (29 de dezembro de 2018): 1045–54. http://dx.doi.org/10.1177/0959651818821448.

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This article addresses a flight-stability problem for the multiple unmanned aerial vehicles cooperative formation flight in the process of the closed and high-speed flight. The main objective is to design a cooperative formation controller with known external factors, and this controller can keep the consensus of attitude and position and reduce the communication delay between any two unmanned aerial vehicles and increase unmanned aerial vehicles formation cruise time under the known external factors. Known external factors are taken into consideration, and longitude maneuvers using nonlinear thrust vectors were employed with unsteady aerodynamic models, according to the attitude and position of unmanned aerial vehicles, which were employed as corresponding input signals for studying the dynamic characteristics of unmanned aerial vehicles formation flight. In addition, the relative distance between any two unmanned aerial vehicles was not allowed to exceed their safe distance so that the controller could perform collision avoidance. An analysis of formation flight distance error shows that it converged to a fixed value that well ensured unmanned aerial vehicles formation flight stability. The experimental results show that the controller can improve the speed of a closed formation effectively and maintain the stability of formation flight, which provides a method for closed formation flight controller design and collision avoidance for any two unmanned aerial vehicles. Meanwhile, the effectiveness of proposed controller is fully proved by semi-physical simulation platform.

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13

Zhang, Zhouyu, Yunfeng Cao, Meng Ding, Likui Zhuang e Jiang Tao. "Vision-based guidance for fixed-wing unmanned aerial vehicle autonomous carrier landing". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, n.º 8 (25 de julho de 2018): 2894–913. http://dx.doi.org/10.1177/0954410018788003.

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Autonomous carrier landing is regarded as a crucial problem among the flight stages of carrier-based unmanned aerial vehicle. In recent years, vision-based guidance has become a promising solution for unmanned aerial vehicle autonomous carrier landing. In this paper a new vision-based navigation scheme is proposed for unmanned aerial vehicle autonomous carrier landing. The scheme aims at dealing with two core problems: searching the carrier by using the images obtained from the airborne forward-looking camera and estimating the relative position and attitude between the unmanned aerial vehicle and the carrier. In order to solve the first problem, the spectral residual-based saliency analysis method is firstly adopted to obtain the Region of Interest. Then the locality-constraint linear coding-based feature learning method is proposed for feature extraction, and the region of interest containing the carrier is finally recognized by the linear support vector machine. In order to solve the second problem, five feature points are firstly selected on the surface of the carrier. Then, a new carrier-fixed moving reference coordinate system is set up. The six landing parameters including three attitude parameters and three position parameters are finally obtained by using orthogonal iteration. The experiment results verify the superiority and effectiveness of the algorithms proposed in this paper.

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14

Sutthison, Danupol, Prasatporn Wongkamchang e Nukul Sukuprakarn. "Aerodynamic Studies of Small Box-Wing Unmanned Aerial Vehicle Using CFD". Journal of Physics: Conference Series 2235, n.º 1 (1 de maio de 2022): 012070. http://dx.doi.org/10.1088/1742-6596/2235/1/012070.

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Abstract This paper presents a computational fluid dynamics (CFD) simulation study of a small unmanned aerial vehicle (UAV) with airfoil s3010 and 245 mm chord length at a cruising speed of 17.5 m/s, compared with the aerodynamic characteristics of a 3D conventional fixed-wing UAV from a commercial RC airplane modified with a box-wing configuration. Simulation results showed that at an angle of attack of 0°, the lift coefficient increased by 60.005%, drag coefficient increased by 58.3299% and L/D ratio increased 1.0578%. The box-wing UAV had higher lift-to-drag ratio than the fixed-wing UAV. However, weight increased by 46.5%. The fuselage shape of the box-wing UAV in this study can be redesigned to shorten the rear area for drag and weight reduction.

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15

Kayacan, Erdal, Mojtaba Ahmadieh Khanesar, Jaime Rubio-Hervas e Mahmut Reyhanoglu. "Learning Control of Fixed-Wing Unmanned Aerial Vehicles Using Fuzzy Neural Networks". International Journal of Aerospace Engineering 2017 (2017): 1–12. http://dx.doi.org/10.1155/2017/5402809.

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A learning control strategy is preferred for the control and guidance of a fixed-wing unmanned aerial vehicle to deal with lack of modeling and flight uncertainties. For learning the plant model as well as changing working conditions online, a fuzzy neural network (FNN) is used in parallel with a conventional P (proportional) controller. Among the learning algorithms in the literature, a derivative-free one, sliding mode control (SMC) theory-based learning algorithm, is preferred as it has been proved to be computationally efficient in real-time applications. Its proven robustness and finite time converging nature make the learning algorithm appropriate for controlling an unmanned aerial vehicle as the computational power is always limited in unmanned aerial vehicles (UAVs). The parameter update rules and stability conditions of the learning are derived, and the proof of the stability of the learning algorithm is shown by using a candidate Lyapunov function. Intensive simulations are performed to illustrate the applicability of the proposed controller which includes the tracking of a three-dimensional trajectory by the UAV subject to time-varying wind conditions. The simulation results show the efficiency of the proposed control algorithm, especially in real-time control systems because of its computational efficiency.

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Zheng, Tiancheng. "Current Status and Prospect of Aquatic-aerial Unmanned Vehicles". Highlights in Science, Engineering and Technology 46 (25 de abril de 2023): 125–33. http://dx.doi.org/10.54097/hset.v46i.7693.

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As people have higher and higher requirements for water-air detection and communication, the research of aquatic-aerial unmanned vehicles with high flexibility and maneuverability has become more and more in-depth. In this paper, the aquatic-aerial unmanned vehicles is classified according to their driving modes and constructions, and the aquatic-aerial unmanned vehicles is divided into multi-rotor vehicles, fixed-wing vehicles and bionic principle driven vehicles. This paper will give the readers a detailed and comprehensive introduction to the aquatic-aerial unmanned vehicles. In this paper, the aquatic-aerial unmanned vehicles is classified according to their driving modes and constructions, and the aquatic-aerial unmanned vehicles is divided into multi-rotor vehicles, fixed-wing vehicles and bionic principle driven vehicles, and the driving principle and operation mode of each type of aquatic-aerial unmanned vehicles are introduced. At the same time, the application of aquatic-aerial unmanned vehicles in different scenarios is analyzed, so that readers can have some reference when they need to buy or develop aquatic-aerial unmanned vehicles.

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Majid, Abdul, Raden Sumiharto e Setyawan Bekti Wibisono. "Identifikasi Model dari Pesawat Udara Tanpa Awak Sayap Tetap Jenis Bixler". IJEIS (Indonesian Journal of Electronics and Instrumentation Systems) 5, n.º 1 (1 de maio de 2015): 43. http://dx.doi.org/10.22146/ijeis.7152.

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AbstrakModel terbang merupakan bagian penting dalam pembangunan sistem kontrol suatu pesawat udara tanpa awak sayap tetap, terutama dalam pembangunan sistem kendali mandiri atau autopilot pesawat. Dengan model terbang, gerak terbang pesawat dapat direpresentasikan dan disimulasikan. Pada penelitian ini, model terbang dihasilkan melalui identifikasi sistem atau pemodelan pesawat udara tanpa awak sayap tetap jenis Bixler. Identifikasi sistem dilakukan berdasarkan eksperimen (pengambilan data terbang) dan digunakan struktur model state-space. Terdapat tiga tahapan dalam penelitian ini, pemodelan gerak terbang pesawat, pengambilan data terbang, dan identifikasi model terbang. Melalui tiga tahapan tersebut, diperoleh model terbang pesawat sayap tetap jenis Bixler yang dapat merepresentasikan gerak terbang pesawat yang terbagi dalam 2 mode, mode longitudinal dan mode lateral.Diperoleh model terbang mode longitudinal pesawat udara tanpa awak sayap tetap jenis Bixler menggunakan 13 parameter menggunakan struktur model state-space orde 4. Model terbang mode lateral pesawat udara tanpa awak sayap tetap jenis Bixler menggunakan 11 parameter menggunakan struktur model state-space orde 4. Kata kunci—UAV, Identifikasi Sistem, Pemodelan AbstractFlight model is one of importing thing in fixed-wing unmanned aerial vehicle (UAV) control system development, mainly in the aircraft autopilot. Through this flight model, the aircraft motion can be represented and simulated.In this research, the flight model is obtained through system identification and system modelling of Bixler fixed-wing unmanned aerial vehicle. System identification is based on experiment data and use state-space model structure. There are three stages in this research, aircraft motion system modelling, flight data collecting, and flight model identification. Through those three stages, Bixler fixed-wing unmanned aerial vehicle flight model is obtained as represented in two modes, longitudinal mode and lateral modeThe Bixler fixed-wing unmanned aerial vehicle longitudinal mode flight model is obtained using 13 parameters. The lateral mode is obtained using 11 parameters. All modes are in 4th order state space model structure. Keywords— UAV, System Identification, Modelling

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Verstraete, Dries, Jennifer L. Palmer e Mirko Hornung. "Preliminary Sizing Correlations for Fixed-Wing Unmanned Aerial Vehicle Characteristics". Journal of Aircraft 55, n.º 2 (março de 2018): 715–26. http://dx.doi.org/10.2514/1.c034199.

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Levin, Joshua M., Aditya A. Paranjape e Meyer Nahon. "Agile maneuvering with a small fixed-wing unmanned aerial vehicle". Robotics and Autonomous Systems 116 (junho de 2019): 148–61. http://dx.doi.org/10.1016/j.robot.2019.03.004.

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Fan, YanMing, Meng Ding e YunFeng Cao. "Vision algorithms for fixed-wing unmanned aerial vehicle landing system". Science China Technological Sciences 60, n.º 3 (7 de fevereiro de 2017): 434–43. http://dx.doi.org/10.1007/s11431-016-0618-3.

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S, Priyashree, Praveen Prabhu, Mahesh R, Nandeesh D K e Jayanth A. Kanago. "Military Based Fixed Wing Scouting of an Unmanned Aerial Vehicle". International Journal for Research in Applied Science and Engineering Technology 11, n.º 3 (31 de março de 2023): 935–44. http://dx.doi.org/10.22214/ijraset.2023.49564.

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Abstract: Unmanned Aerial Vehicles (UAV) is in constant development since First World War. As the technology became complex and compact, the UAVs are also being utilized for commercial purposes. The main purpose of a UAV was for scouting, to perform certain operations in remote areas with minimal human interference and to eliminate the risk of human pilots. UAVs are classified based on their weight, range of operation, type of model, and fuel consumption. At present, multi-rotor drones with high mobility are widely used for commercial sectors especially, aerial photography, sports, surveys, etc. Most of the drones are electric-based which provide a maximum of 30 minutes flight time that is sufficient for small scale applications. There are combustible fuel based drones in development, but they are very expensive, also multi-rotor drones are inefficient and provide less output per input.

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Liang, Zhuang, Li Fan, Guangwei Wen e Zhixiong Xu. "Design, Modeling, and Control of a Composite Tilt-Rotor Unmanned Aerial Vehicle". Drones 8, n.º 3 (16 de março de 2024): 102. http://dx.doi.org/10.3390/drones8030102.

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Tilt-rotor unmanned aerial vehicles combine the advantages of multirotor and fixed-wing aircraft, offering features like rapid takeoff and landing, extended endurance, and wide flight conditions. This article provides a summary of the design, modeling, and control of a composite tilt-rotor. During modeling process, aerodynamic modeling was performed on the tilting and non-tilting parts based on the subcomponent modeling method, and CFD simulation analysis was conducted on the entire unmanned aerial vehicle to obtain its accurate aerodynamic characteristics. In the process of modeling the motor propeller, the reduction of motor thrust and torque due to forward flow and tilt angle velocity is thoroughly examined, which is usually ignored in most tilt UAV propeller models. In the controller design, this paper proposes a fusion ADRC control strategy suitable for vertical takeoff and landing of this type of tiltrotor. The control system framework is built using Simulink, and the control algorithm’s efficiency has been verified through simulation testing. Through the proposed control scheme, it is possible for the composite tiltrotor unmanned aerial vehicle to smoothly transition between multirotor and fixed-wing flight modes.

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Zhang, S., Z. Wang, Y. Wu e Y. Yu. "Flight dynamic coupling analysis of a bio-inspired elastic-wing aircraft". Aeronautical Journal 122, n.º 1250 (25 de março de 2018): 572–97. http://dx.doi.org/10.1017/aer.2018.11.

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ABSTRACTIt is a challenge for small, fixed-wing aerial vehicles to maintain flight stability under gusts. Inspired by the geometric features and the structural dynamic characteristics of the gliding bird wing, an elastic wing with similar characteristics was designed and optimised for use as part of unmanned aerial vehicle. A flight dynamic model, which includes the coupling of the longitudinal flight modes and the aeroelastic modes of the flexible wing, was built to analyse the mechanisms of specific coupling for the structural characteristics of the wing design, and how these specific couplings affect flight dynamics. The results showed that the bio-inspired elastic wing effectively allows alleviation of the gust response of the prototype through coupling effects of the short period and the first aeroelastic mode, even with a considerable frequency gap. These effects become more significant when the airspeed becomes larger. The conclusions of this research can facilitate further development of bird-sized unmanned aerial vehicles to extend their applications and make these vehicles more adaptive for flight in complex atmospheric environments.

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Sun, Yun Ping, L. T. Wu e Yen Chu Liang. "Stability Derivatives Estimation of Unmanned Aerial Vehicle". Key Engineering Materials 381-382 (junho de 2008): 137–40. http://dx.doi.org/10.4028/www.scientific.net/kem.381-382.137.

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The purpose of this research is to estimate the dimensional stability derivatives in linear dynamic model of a fixed-wing model-scale unmanned aerial vehicle (UAV) by real flight data logged by an onboard flight computer. The paper described the experimental setup, operation procedure of raw flight data, process of nonlinear least squares estimation, and cause-effect examination of impulse responses. The simulation-based results of the estimated model indicated a very good accuracy with real flight data. The linear longitudinal and lateral models are very helpful for designing the stability-augmentation system or autopilot for the UAV.

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A, Kaviyarasu, Saravanakumar A e Rajesh G. "HILS based Waypoint Simulation for Fixed Wing Unmanned Aerial Vehicle (UAV)". Defence Science Journal 72, n.º 5 (1 de novembro de 2022): 687–94. http://dx.doi.org/10.14429/dsj.72.17952.

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Hardware in loop simulation HILS-based waypoint simulation for fixed wing unmanned aerial vehicles is proposed in this paper. It uses an open-source arducopter as a flight controller, mission planner, and X-plane simulator. Waypoint simulation is carried out in the flight controller and executed in an X-plane simulator through a mission planner. A fixed wing unmanned aerial vehicle with an inverted T tail configuration has been chosen to study and validate waypoint flight control algorithms. The data transmission between mission planner and flight controller is done by serial protocol, whereas data exchange between X-plane and mission planner is done by User Datagram Protocol (UDP). APM mission planner is used as a machine interface to exchange data between the flight controller and the user. User inputs and flight gain parameters, both inner loop and outer loop, can be modified with the help of a mission planner. In addition to that, the mission planner provides a visual output representation of flight data and navigation algorithm.

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Wang, Tianyi, Luxin Zhang e Zhihua Chen. "Robust Control for Underactuated Fixed-Wing Unmanned Aerial Vehicles". Mathematics 12, n.º 7 (8 de abril de 2024): 1118. http://dx.doi.org/10.3390/math12071118.

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Dynamic surface control (DSC) is a recognized nonlinear control approach for high-order systems. However, as the complexity of the system increases and the first-order filter (FOF) is introduced, there exists a singularity problem, i.e., the control input will reach infinity. This limits the application of the DSC algorithm to a class of real-world systems with complex dynamics. To address the problem of singularity, we present a novel DSC approach called nonsingular dynamic surface control (NDSC), which completely avoids the singularity problem and significantly improves the overall control performance. NDSC includes a nonsingular hypersurface, which is constructed by the error between system states and virtual control inputs. Then the nonsingular hypersurface will be applied to derive the corresponding control law with the aid of the DSC approach to ensure the output of the system can track arbitrary desired trajectories. NDSC has the following novel features: (1) finite time asymptotic stabilization can be guaranteed; (2) the performance of NDSC is insensitive to the FOF’s parameter variation once the maximum tracking error of FOF is bounded, which significantly reduces reliance on the control sampling frequency. We thoroughly evaluate the proposed NDSC algorithm in an unmanned aerial vehicle (UAV) system with an underactuated nature. Finally, the simulation results illustrate and highlight the effectiveness and superiority of the proposed control algorithm.

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Xiaoqian, Tang, Zhao Feicheng, Tang Zhengbing e Wang Hongying. "Nonlinear Extended Kalman Filter for Attitude Estimation of the Fixed-Wing UAV". International Journal of Optics 2022 (1 de fevereiro de 2022): 1–9. http://dx.doi.org/10.1155/2022/7883851.

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Flying vehicle’s navigation, direction, and control in real-time results in the design of a strap-down inertial navigation system (INS). The strategy results in low accuracy, performance with correctness. Aiming at the attitude estimation problem, many data fusion or filtering methods had been applied, which fail in many cases, which attains the nonlinear measurement model, process dynamics, and high navigation range. The main problem in unmanned aerial vehicles (UAVs) and flying vehicles is the determination of attitude angles. A novel attitude estimation algorithm is proposed in this study for the unmanned aerial vehicle (UAV). This research article designs two filtering algorithms for fixed-wing UAVs which are nonlinear for the attitude estimation. The filters are based on Kalman filters. The unscented Kalman filter (UKF) and cubature Kalman filter (CKF) were designed with different parameterizations of attitude, i.e., Euler angle (EA) and INS/unit quaternion (UQ) simultaneously. These filters, EA-UKF and INS-CKF, use the nonlinear process and measurement model. The computational results show that among both filters, the CKF attains a high accuracy, robustness, and estimation for the attitude estimation of the fixed-wing UAV.

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Chen, Chao, Jiyang Zhang, Daibing Zhang e Lincheng Shen. "Control and flight test of a tilt-rotor unmanned aerial vehicle". International Journal of Advanced Robotic Systems 14, n.º 1 (1 de janeiro de 2017): 172988141667814. http://dx.doi.org/10.1177/1729881416678141.

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Tilt-rotor unmanned aerial vehicles have attracted increasing attention due to their ability to perform vertical take-off and landing and their high-speed cruising abilities, thereby presenting broad application prospects. Considering portability and applications in tasks characterized by constrained or small scope areas, this article presents a compact tricopter configuration tilt-rotor unmanned aerial vehicle with full modes of flight from the rotor mode to the fixed-wing mode and vice versa. The unique multiple modes make the tilt-rotor unmanned aerial vehicle a multi-input multi-output, non-affine, multi-channel cross coupling, and nonlinear system. Considering these characteristics, a control allocation method is designed to make the controller adaptive to the full modes of flight. To reduce the cost, the accurate dynamic model of the tilt-rotor unmanned aerial vehicle is not obtained, so a full-mode flight strategy is designed in view of this situation. An autonomous flight test was conducted, and the results indicate the satisfactory performance of the control allocation method and flight strategy.

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Muhammed, Manaf, e Muhammad Shakeel Virk. "Ice Accretion on Fixed-Wing Unmanned Aerial Vehicle—A Review Study". Drones 6, n.º 4 (28 de março de 2022): 86. http://dx.doi.org/10.3390/drones6040086.

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Ice accretion on commercial aircraft operating at high Reynolds numbers has been extensively studied in the literature, but a direct transformation of these results to an Unmanned Aerial Vehicle (UAV) operating at low Reynolds numbers is not straightforward. Changes in Reynolds number have a significant impact on the ice accretion physics. Previously, only a few researchers worked in this area, but it is now gaining more attention due to the increasing applications of UAVs in the modern world. As a result, an attempt is made to review existing scientific knowledge and identify the knowledge gaps in this field of research. Ice accretion can deteriorate the aerodynamic performance, structural integrity, and aircraft stability, necessitating optimal ice mitigation techniques. This paper provides a comprehensive review of ice accretion on fixed-wing UAVs. It includes various methodologies for studying and comprehending the physics of ice accretion on UAVs. The impact of various environmental and geometric factors on ice accretion physics is reviewed, and knowledge gaps are identified. The pros and cons of various ice detection and mitigation techniques developed for UAVs are also discussed.

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Hosen, Jesper, Håkon H. Helgesen, Lorenzo Fusini, Thor I. Fossen e Tor A. Johansen. "Vision-Aided Nonlinear Observer for Fixed-Wing Unmanned Aerial Vehicle Navigation". Journal of Guidance, Control, and Dynamics 39, n.º 8 (agosto de 2016): 1777–89. http://dx.doi.org/10.2514/1.g000281.

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Zhai, Ruiyong, Zhaoying Zhou, Wendong Zhang, Shengbo Sang e Pengwei Li. "Control and navigation system for a fixed-wing unmanned aerial vehicle". AIP Advances 4, n.º 3 (março de 2014): 031306. http://dx.doi.org/10.1063/1.4866169.

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Ding, Jicheng, Kai Zou e Junling Zhang. "A Combined Control Strategy for Fixed-Wing Unmanned Aerial Vehicles". Journal of Computational and Theoretical Nanoscience 13, n.º 10 (1 de outubro de 2016): 7199–211. http://dx.doi.org/10.1166/jctn.2016.5692.

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This study proposes a combined proportional–integral–derivative (PID) flight control strategy within a fixed-wing unmanned aerial vehicle (UAV). This type of UAV has high speed and high maneuverability. Considering relatively simple implementation, low computational effort, and intuitive operation, the classic PID controller is still popular but imperfect because of several well-known reasons. A number of practical and improved PID control methods, such as integral separation, anti-windup, and gearshift integral, are always used separately in many control fields. In this study, the combined PID flight control strategy is designed and applied to promote the classic PID control performance, along with the aforementioned methods, to fixed-wing UAV. The proposed approach adopts different controls depending on the deviation outputs and UAV physical limitations. The design flowchart and flight control loop are also presented. The combined PID flight control strategy can achieve a smaller overshoot and a shorter settling time than the conventional PID control. Comparable typical flight parameter tracking results (i.e., pitch, roll, altitude, and path angle) from principle simulation, hardware-in-the-loop simulation, and real flight experiment validate the efficacy and practicability of the combined PID flight control strategy.

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Zhao, Yunyun, Xiangke Wang, Yirui Cong e Lincheng Shen. "Information geometry-based action decision-making for target tracking by fixed-wing unmanned aerial vehicle". International Journal of Advanced Robotic Systems 15, n.º 4 (1 de julho de 2018): 172988141878706. http://dx.doi.org/10.1177/1729881418787061.

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In this article, we study the ground moving target tracking problem for a fixed-wing unmanned aerial vehicle equipped with a radar. This problem is formulated in a partially observable Markov process framework, which contains the following two parts: in the first part, the unmanned aerial vehicle utilizes the measurements from its radar and employs a Kalman filter to estimate the target’s real-time location; in the second part, the unmanned aerial vehicle optimizes its trajectory in a real-time manner so that the radar’s measurements can include more useful information. To solve the trajectory optimization problem, we proposed an information geometry-based partially observable Markov decision process method. Specifically, the cumulative amount of information in the observation is represented by Fisher information of information geometry, and acts as the criterion of the partially observable Markov decision process problem. Furthermore, to guarantee the real-time performance, an important trade-off between the optimality and computation cost is made by an approximate receding horizon approach. Finally, simulation results corroborate the accuracy and time-efficiency of our proposed method and also show our advantage in computation time compared to existing methods.

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Papadopoulos, C., S. Vlachos e K. Yakinthos. "Conceptual design of a fixed wing hybrid UAV UUV platform". IOP Conference Series: Materials Science and Engineering 1226, n.º 1 (1 de fevereiro de 2022): 012028. http://dx.doi.org/10.1088/1757-899x/1226/1/012028.

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Abstract In this work, the conceptual design methodology of a hybrid Unmanned Aerial Vehicle (UAV) – Unmanned Underwater Vehicle (UUV) platform is presented. As the mission complexity and the need for interoperability between different platforms grows more demanding by the day, hybrid platforms are becoming an essential solution. Hybrid UAV-UUVs can operate seamlessly and repeatedly in both the aerial and underwater environments, something that numerous animal species already execute in an optimized way. The design methodology starts with the review of the few available prototypes, creating initial design trends and continues with analytical calculations. These calculations are based on aircraft design textbooks and are modified to take into account the special characteristics of a hybrid platform, such as the means of transition between the water and the air. A Blended Wing Body (BWB) layout configuration is selected for the numerous aerodynamic advantages that it offers. The analytical calculations are then validated with the use of high fidelity CFD calculations. The results from the conceptual design phase indicate that the proposed methodology for hybrid UAV-UUV configurations provides a good design accuracy. Finally, the outcome of this methodology, which is a hybrid UAV-UUV platform is potentially the answer to the operational gap for missions that include both underwater and aerial environments.

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Ansyori, Ade Firli, e Anton Yudhana. "Implementasi Waypoint Menggunakan GPS pada UAV untuk Mendapatkan Akurasi Terbaik dengan Pengontrol PID". Buletin Ilmiah Sarjana Teknik Elektro 3, n.º 3 (6 de abril de 2022): 210–20. http://dx.doi.org/10.12928/biste.v3i3.4851.

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Unmanned Aerial Vehicles (UAV) is an unmanned aerial vehicle from a technical point of view, a UAV can be defined as an aircraft equipped with the necessary data processing units, sensors, automatic control, and communication systems, and capable of performing autonomous flight missions without manual intervention. This research is a research development and testing of the capabilities of fixed-wing aircraft, on flight missions, fixed-wing aircraft are often less precise so the accuracy of UAV flights is very influential in the intended coordinate mission in determining flight accuracy by following the coordinate point data provided obtained via GPS (Global Positioning System) can be minimized by setting the value of the PID manually on the Mission Planner so that the fixed-wing aircraft vehicle can go to its destination with precision at a predetermined coordination point. tracking can follow the desired coordinate point. With a PID value of P:0.65 I:0.3, D:6. The error distance generated by the fixed-wing aircraft from each coordinate point destination that has been given to the mission planner gets an error distance value of ± 3 m, with a level of precision in the Good category or the medium category. Unmanned Aerial Vehicles (UAV) merupakan salah satu wahana tanpa awak di udara dari sudut pandang teknis, UAV dapat didefinisikan sebagai pesawat yang dilengkapi dengan unit pengolah data yang diperlukan, sensor, sistem kontrol dan komunikasi otomatis, dan mampu melakukan misi penerbangan otonomus tanpa intervensi manual. Penelitian ini merupakan penelitian pengembangan dan menguji kemampuan wahana pesawat fixed-wings, pada misi penerbangan wahana pesawat fixed-wing sering kali kurang presisi sehingga keakuratan pada penerbangan UAV sangat berpengaruh dalam suatu misi koordinat yang dituju, sehingga dalam menentukan keakurasian penerbangan dengan mengikuti data titik koordinasi yang di dapatkan melalui GPS (Global Positioning System) dapat diminimalisi dengan mengatur nilai dari PID-nya secara manual pada Mission Planner, sehingga wahana pesawat fixed-wing dapat menuju lokasi tujuannya dengan presisi pada titik koordinasi yang telah di tentukan., Dari simulasi penelitian diperoleh proses tracking dapat mengikuti titik koordinat yang diinginkan. Dengan nilai PID sebesar P:0.65 I:0.3, D:6. Jarak error yang dihasilkan dari wahana pesawat fixed-wings dari setiap tujuan titik koordinat yang telah diberikan pada mission planner mendapatkan nilai jarak error ± 3 m, dengan tingkatan presisi pada katagori Good atau katagori yang sedang.

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Brouwer, Ronald L., Matthieu A. de Schipper, Patrick F. Rynne, Fiona J. Graham, Ad J. H. M. Reniers e Jamie H. MacMahan. "Surfzone Monitoring Using Rotary Wing Unmanned Aerial Vehicles". Journal of Atmospheric and Oceanic Technology 32, n.º 4 (abril de 2015): 855–63. http://dx.doi.org/10.1175/jtech-d-14-00122.1.

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AbstractThis study investigates the potential of rotary wing unmanned aerial vehicles (UAVs) to monitor the surfzone. This paper shows that these UAVs are extremely flexible surveying platforms that can gather near-continuous moderate spatial resolution and high temporal resolution imagery from a fixed position high above a study site. The rotary wing UAVs used in this study can fly for ~12 min with a mean loiter radius of 1–3.5 m and a mean loiter error of 0.75–4.5 m. These numbers depend on the environmental conditions, flying style, battery type, and vehicle type. The images obtained from the UAVs, and in combination with surveyed ground control points (GCPs), can be georectified to a pixel resolution between 0.01 and 1 m, and a reprojection error—that is, the difference between the surveyed GPS location of a GCP and the location of the GCP obtained from the georectified image—of O(1 m). The flexibility of rotary wing UAVs provides moderate spatial resolution and high temporal resolution imagery, which are highly suitable to quickly obtain surfzone and beach characteristics in response to storms or for day-to-day beach safety information, as well as scientific pursuits of surfzone kinematics on different spatial and temporal scales, and dispersion and advection estimates of pollutants.

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Ariyanto, Mochammad, Joga D. Setiawan, Teguh Prabowo, Ismoyo Haryanto e Munadi. "Design of a Low-Cost Fixed Wing UAV". MATEC Web of Conferences 159 (2018): 02045. http://dx.doi.org/10.1051/matecconf/201815902045.

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This research will try to design a low cost of fixed-wing unmanned aerial vehicle (UAV) using low-cost material that able to fly autonomously. Six parameters of UAV’s structure will be optimized based on basic airframe configuration, wing configuration, straight wing, tail configuration, fuselage material, and propeller location. The resulted and manufactured prototype of fixed-wing UAV will be tested in autonomous fight tests. Based on the flight test, the developed UAV can successfully fly autonomously following the trajectory command. The result shows that low-cost material can be used as a body part of fixed-wing UAV.

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Yu, Jiawen. "Design and Optimization of Wing Structure for a Fixed-Wing Unmanned Aerial Vehicle (UAV)". Modern Mechanical Engineering 08, n.º 04 (2018): 249–63. http://dx.doi.org/10.4236/mme.2018.84017.

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Ismail, Nabila, e Khairul Nizam Tahar. "Extraction of Building Footprints from Different Unmanned Aerial Vehicle (UAV) Platforms". International Journal of Engineering & Technology 7, n.º 4.25 (30 de novembro de 2018): 67–71. http://dx.doi.org/10.14419/ijet.v7i4.25.22249.

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The demand for map updating is increasing especially for developing countries. Therefore, rapid data acquisition of an urban area is needed. This study proposes unmanned platform as one of the solutions for rapid data acquisition to update the map for developing countries. The objective of this study is to perform the extraction of building footprints using fixed-wing unmanned aerial vehicle (UAV) and multi-rotor UAV. All images acquired from both UAVs were processed using different image matching algorithms to perform relative orientation. The building footprints were extracted based on different orthophoto results. The building footprints were evaluated in terms of area and length. The results show the area based matching method records the accurate result in term of area and length assessment which are about 13m2 and 1.4m respectively. The results also show the multirotor provides the accurate results compared to fixed wing platform. The outcome could be used for specific applications such as urban expansion changes and land cover change detection.Â Â

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Sterligov, Boris, e Sergei Cherkasov. "Reducing Magnetic Noise of an Unmanned Aerial Vehicle for High-Quality Magnetic Surveys". International Journal of Geophysics 2016 (2016): 1–7. http://dx.doi.org/10.1155/2016/4098275.

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The use of light and ultralight unmanned aerial vehicles (UAVs) for magnetic data acquisition can be efficient for resolving multiple geological and engineering tasks including geological mapping, ore deposits’ prospecting, and pipelines’ monitoring. The accuracy of the aeromagnetic data acquired using UAV depends mainly on deviation noise of electric devices (engine, servos, etc.). The goal of this research is to develop a nonmagnetic unmanned aerial platform (NUAP) for high-quality magnetic surveys. Considering parameters of regional and local magnetic survey, a fixed-wing UAV suits geological tasks better for plain area and copter type for hills and mountains. Analysis of the experimental magnetic anomalies produced by a serial light fixed-wing UAV and subsequent magnetic and aerodynamic modeling demonstrates a capacity of NUAP with internal combustion engine carrying an atomic magnetic sensor mounted on the UAV wings to facilitate a high-quality magnetic survey.

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Kim, Kijoon, Seungkeun Kim, Jinyoung Suk, Jongmin Ahn, Nakwan Kim e Byoung-Soo Kim. "Flight test of flying-wing type unmanned aerial vehicle with partial wing-loss". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, n.º 5 (21 de fevereiro de 2018): 1611–28. http://dx.doi.org/10.1177/0954410018758497.

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This paper investigates experimental evaluation via flight tests for applying adaptive neural network controller to a flying-wing type unmanned aerial vehicle experiencing partial wing-loss. For this, six-degree-of-freedom numerical model is constructed taking into account damage-induced changes to the unmanned aerial vehicle in aerodynamic coefficients, mass, center of gravity, and moments of inertia. Numerical simulations are performed to investigate the flight dynamics change and to verify the performance of the neural network based controller. During the flight test, main wing-loss is artificially generated by 22% or 33% area moment. The flight test verifies that the damaged unmanned aerial vehicle shows drastic roll behavior with the unstable longitudinal response, and the neural network based adaptive controller combined with feedback linearization successfully compensates for the wing damage.

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Pargaonkar, Jay. "A Systematic Design of an Unmanned Aerial Vehicle for Surveillance Applications". International Journal of Engineering Research in Electrical and Electronics Engineering 9, n.º 5 (14 de maio de 2022): 8–11. http://dx.doi.org/10.36647/ijereee/09.05.a002.

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In the past few years, the demand for Unmanned Aerial Vehicles, more commonly known as drones, has increased exponentially. This is mostly because they have huge applications in various areas like mapping, surveillance, payload delivery, aerial photography, wildlife surveillance, etc. VTOL, or Vertical Takeoff and Landing is a concept in which an aircraft or a UAV takes off and lands vertically. This concept has its own advantages over traditional fixed wing takeoff and landing systems. It does not require a large strip of land for takeoff, and the required lift can be generated from the thrust produced by the motors. It also enables a better and smoother landing than conventional fixed-wing systems. This paper presents a design for a quadcopter UAV system which can be used for surveillance in various disciplines. A unique concept of a hybrid frame has been introduced. This largely improves the stability and reduces vibrations to a great extent. Surveillance is carried out using Python, which detects objects using OpenCV and the YOLO algorithm

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Zafirov, Dimo. "Electric vertical take-off and landing fixed wing unmanned aerial vehicle for long endurance or long range?" Aerospace Research in Bulgaria 31 (2019): 99–107. http://dx.doi.org/10.3897/arb.v31.e08.

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An analysis of requirements to electric vertical take-off and landing unmanned aerial vehicle with fixed wings is carried out in this article. These aircraft have to fulfil requirements of users and to be convenient for operation in any field conditions. Long flight duration and long flight range are important for most missions. Mathematical models for both cases are presented and it has been found that the requirements for the wing load are different. It is recommended to use a type of UAV (Unmanned Aerial Vehicle) that is modular and allows performing flights with different configurations and payload depending on the mission in order to fulfill these requirements.

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Zhao, Wenjie, Zhou Fang e Ping Li. "Bridging GPS Outages for Fixed-wing Unmanned Aerial Vehicles". Journal of Navigation 68, n.º 2 (23 de setembro de 2014): 308–26. http://dx.doi.org/10.1017/s0373463314000599.

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This paper reports on a new navigation algorithm for fixed-wing Unmanned Aerial Vehicles (UAVs) to bridge Global Position System (GPS) outages, based on a common navigation system configuration. The ground velocity is obtained from wind-compensated airspeed, and a centripetal force model is introduced to estimate the motion acceleration. Compensated by this acceleration, the gravity vector can be extracted from the accelerometer measurement. Finally, fusing the information of the ground velocity, magnetic heading, barometric height, and gravity vector, the Integrated Navigation System (INS) is reconstructed, and an Extended Kalman Filter (EKF) is used to estimate INS errors. Hardware-in-loop simulation results show that compared with INS-only solutions, the proposed method effectively resists long-term drift of INS errors and significantly improves the accuracy for dynamic navigation during GPS outages.

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de Ruiter, A. H. J., e S. Owlia. "Autonomous obstacle avoidance for fixed-wing unmanned aerial vehicles". Aeronautical Journal 119, n.º 1221 (novembro de 2015): 1415–36. http://dx.doi.org/10.1017/s0001924000011325.

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AbstractThis paper investigates a method for autonomous obstacle avoidance for fixed-wing unmanned aerial vehicles (UAVs), utilising potential fluid flow theory. The obstacle avoidance algorithm needs only compute the instantaneous local potential velocity vector, which is passed to the flight control laws as a direction command. The approach is reactive, and can readily accommodate real-time changes in obstacle information. UAV manoeuvring constraints on turning or pull-up radii, are accounted for by approximating obstacles by bounding rectangles, with wedges added to their front and back to shape the resulting fluid pathlines. It is shown that the resulting potential flow velocity field is completely determined by the obstacle field geometry, allowing one to determine a non-dimensional relationship between obstacle added wedge-length and the corresponding minimum pathline radius of curvature, which can then be readily scaled in on-board implementation. The efficacy of the proposed approach has been demonstrated numerically with an Aerosonde UAV model.

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Darlami, Kamal, Aditya Amatya, Bikash Kunwar, Sanjeeb Poudel e Ujwal Dhakal. "Design and Analysis of Twin-Vertical-Tailed Fixed-Wing Unmanned Aerial Vehicle". Journal of Automation and Automobile Engineering 5, n.º 3 (7 de dezembro de 2020): 12–30. http://dx.doi.org/10.46610/joaaen.2020.v05i03.003.

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Rahino Triputra, Fadjar, Bambang Riyanto Trilaksono, Trio Adiono e Rianto Adhy Sasongko. "Visual Servoing of Fixed - Wing Unmanned Aerial Vehicle Using Command Filtered Backstepping". International Journal on Electrical Engineering and Informatics 7, n.º 4 (31 de dezembro de 2015): 584–604. http://dx.doi.org/10.15676/ijeei.2015.7.4.4.

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Priyambodo, Tri Kuntoro, e Abdul Majid. "Modeling and Simulation of The UX-6 Fixed-Wing Unmanned Aerial Vehicle". Journal of Control, Automation and Electrical Systems 32, n.º 5 (29 de junho de 2021): 1344–55. http://dx.doi.org/10.1007/s40313-021-00754-5.

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Wang, Zhaoyang, Dan Zhao e Yunfeng Cao. "Visual Navigation Algorithm for Night Landing of Fixed-Wing Unmanned Aerial Vehicle". Aerospace 9, n.º 10 (17 de outubro de 2022): 615. http://dx.doi.org/10.3390/aerospace9100615.

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In the recent years, visual navigation has been considered an effective mechanism for achieving an autonomous landing of Unmanned Aerial Vehicles (UAVs). Nevertheless, with the limitations of visual cameras, the effectiveness of visual algorithms is significantly limited by lighting conditions. Therefore, a novel vision-based autonomous landing navigation scheme is proposed for night-time autonomous landing of fixed-wing UAV. Firstly, due to the difficulty of detecting the runway caused by the low-light image, a strategy of visible and infrared image fusion is adopted. The objective functions of the fused and visible image, and the fused and infrared image, are established. Then, the fusion problem is transformed into the optimal situation of the objective function, and the optimal solution is realized by gradient descent schemes to obtain the fused image. Secondly, to improve the performance of detecting the runway from the enhanced image, a runway detection algorithm based on an improved Faster region-based convolutional neural network (Faster R-CNN) is proposed. The runway ground-truth box of the dataset is statistically analyzed, and the size and number of anchors in line with the runway detection background are redesigned based on the analysis results. Finally, a relative attitude and position estimation method for the UAV with respect to the landing runway is proposed. New coordinate reference systems are established, six landing parameters, such as three attitude and three positions, are further calculated by Orthogonal Iteration (OI). Simulation results reveal that the proposed algorithm can achieve 1.85% improvement of AP on runway detection, and the reprojection error of rotation and translation for pose estimation are 0.675∘ and 0.581%, respectively.

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Puopolo, Michael, e J. D. Jacob. "Model for Longitudinal Perch Maneuvers of a Fixed-Wing Unmanned Aerial Vehicle". Journal of Aircraft 52, n.º 6 (novembro de 2015): 2021–31. http://dx.doi.org/10.2514/1.c033136.

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