Bibliografie tematiche / Fixed-wing unmanned aerial vehicle

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Letteratura scientifica selezionata sul tema "Fixed-wing unmanned aerial vehicle"

Autore: Grafiati
Pubblicato: 10 agosto 2024

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Articoli di riviste sul tema "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. 5 (dicembre 2016): 909–21. http://dx.doi.org/10.1139/tcsme-2016-0075.

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Abstract (sommario):
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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2

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. 7 (28 marzo 2018): 857–68. http://dx.doi.org/10.1177/0959651818765027.

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Abstract (sommario):
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. 14 (6 agosto 2016): 2628–38. http://dx.doi.org/10.1177/0954410016629692.

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Abstract (sommario):
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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4

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. 2 (9 luglio 2019): 280–93. http://dx.doi.org/10.17509/ijost.v4i2.18185.

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Abstract (sommario):
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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5

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

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Abstract (sommario):
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. 1 (4 maggio 2018): 102–7. http://dx.doi.org/10.30871/jagi.v2i1.738.

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Abstract (sommario):
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. 1 (1 luglio 2023): 012087. http://dx.doi.org/10.1088/1742-6596/2557/1/012087.

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Abstract (sommario):
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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8

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 2014): 436–40. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.436.

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Abstract (sommario):
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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Challa, Vinay Reddy, e Ashwini Ratnoo. "On Maneuverability of Fixed-Wing Unmanned Aerial Vehicle Formations". Journal of Guidance, Control, and Dynamics 44, n. 7 (luglio 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 (settembre 2013): 448–51. http://dx.doi.org/10.4028/www.scientific.net/amr.798-799.448.

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Abstract (sommario):
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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Più fonti

Tesi sul tema "Fixed-wing unmanned aerial vehicle"

1

Fuglaas, Simen. "Precision Airdrop from a Fixed-Wing Unmanned Aerial Vehicle". Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for teknisk kybernetikk, 2014. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-25909.

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Abstract (sommario):
Accurate mapping of the polar regions requires reliable placement ofwireless transmitting sensors, also known as beacons, on icebergs anddrift ice. This thesis considers the use of a specific fixed-wing unmannedaerial vehicle, known as the Penguin B, to accurately deploysaid beacons from the air. An analysis of the possible precision airdropmethods was conducted and the decision was made to release thebeacon in free fall from the aircraft. The estimated trajectory was calculatedand used to decide the optimal release position and direction.Combined this is known as the release configuration. Moreover, twodifferent aircraft path planning algorithms were developed in order toachieve the desired configuration.The final system, including the necessary hardware and software, wasimplemented into the provided framework. This system was furthertested through simulations in the laboratory in addition to some fieldtesting. The simulations revealed that with the most advanced pathplanning algorithm, it was possible to achieve a close to optimal releaseconfiguration. This further resulted in an airdrop where the accuracyof the impact depended primarily on the altitude of release, in additionto the unpredictable environmental factors, such as wind gusts. Thefield tests displayed that the system was successfully implemented intothe provided framework. However, unforeseen technical difficultiesrelated to the aircraft, outside the control of this project, preventedin-air testing.Under the assumptions made throughout this thesis, the simulationsrevealed that the implemented system was able to reliably deploy thebeacon such that it landed within a relatively small perimeter aroundthe target.
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2

Hough, Willem J. "Autonomous aerobatic flight of a fixed wing unmanned aerial vehicle". Thesis, Link to online version, 2007. http://hdl.handle.net/10019/428.

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3

Alberts, Frederik Nicolaas. "Accurate autonomous landing of a fixed-wing unmanned aerial vehicle". Thesis, Stellenbosch : Stellenbosch University, 2012. http://hdl.handle.net/10019.1/71672.

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Abstract (sommario):
Thesis (MScEng)-- Stellenbosch University, 2012.
ENGLISH ABSTRACT: This thesis presents the analysis, design, simulation and practical implementation of a control system to achieve an accurate autonomous landing of a fixed-wing unmanned aerial vehicle in the presence of wind gust atmospheric disturbances. Controllers which incorporate the concept of direct-lift control were designed based on a study of the longitudinal dynamics of the UAV constructed as a testbed. Direct-lift control offers the prospect of an improvement in the precision with which aircraft height and vertical velocity can be controlled by utilising actuators which generate lift directly, instead of the conventional method whereby the moment produced by an actuator results in lift being indirectly generated. Two normal specific acceleration controllers were designed. The first being a conventional moment-based controller, and the second a direct-lift-augmented controller. The moment-based controller makes use of the aircraft’s elevator while the direct-lift augmented controller in addition makes use of the flaps of the aircraft which serve as the direct-lift actuator. Controllers were also designed to regulate the airspeed, altitude, climb rate, and roll angle of the aircraft as well as damp the Dutch roll mode. A guidance controller was implemented to allow for the following of waypoints. A landing procedure and methodology was developed which includes the circuit and landing approach paths and the concept of a glide path offset to calibrate the touchdown point of a landing. All controllers and the landing procedure were tested in a hardware-in-the-loop simulation environment as well as practically in a series of flight tests. Five fully autonomous landings were performed, three of these using the conventional NSA controller, and the final two the direct-lift-augmented NSA controller. The results obtained during the landing flight tests show that the project goal of a landing within five meters along the runway and three meters across the runway was achieved in both normal wind conditions as well as in conditions where wind gusts prevailed. The flight tests also showed that the direct-lift-augmented NSA controller appears to achieve a more accurate landing than the conventional NSA controller, especially in the presence of greater wind disturbances. The direct-lift augmented NSA controller also exhibited less pitch angle rotation during landing.
AFRIKAANSE OPSOMMING: Hierdie tesis verteenwoordig die analise, ontwerp, simulasie en praktiese implementering van ’n beheerstelsel wat ten doel het om ’n akkurate en outonome landing van ’n onbemande vastevlerk vliegtuig in rukwind atmosferiese toestande te bewerkstellig. Gegrond op ’n studie van die longitudinale dinamika van die vliegtuig wat as proeftuig gebruik is, is beheerders ontwerp wat die beginsel van direkte-lig insluit. Direkte-lig beheer hou die potensiaal in om die vliegtuig se hoogte en vertikale snelheid akkuraat te beheer deur gebruik te maak van aktueerders wat lig direk genereer in teenstelling met die konvensionele metode waar die moment van die aktueerder indirek lig genereer. Twee normaal-versnellings beheerders is ontwerp. Die eerste is ’n konvensionele moment-gebaseerde beheerder wat gebruik maak van die hys-aktueerder van die vliegtuig, en die tweede is ’n direkte-lig-bygestaande beheerder wat addisioneel gebruik maak van die flappe van die vliegtuig wat as die direkte-lig aktueerder dien. Vedere beheerders is ontwerp wat die lugspoed, hoogte, klimkoers, en rolhoek van die vliegtuig reguleer asook die “Dutch roll” gedrag afklam. ’n Leiding-beheerder wat die volg van vliegbakens hanteer, is ingestel. Die landingsprosedure en -metodologie is ontwikkel wat die landingspad sowel as die sweef-pad bepaal en wat terselfdertyd ’n metode daarstel om die posisie van die landingspunt te kalibreer. Die beheerders en landingsprosedure is in ’n hardeware-in-die-lus omgewing gesimuleer en deur middel van ’n reeks proefvlugte getoets. Vyf ten volle outonome landings is uitgevoer waarvan drie van die konvensionele normaal-versnellings beheerder gebruik gemaak het, en die laaste twee die direkte-lig-bygestaande normaal-versnellings beheerder. Die vlugtoetsuitslae bevestig dat die navorsingsdoel om ’n landing binne vyf meter in lyn met en drie meter dwarsoor die landingstrook te bewerkstellig, behaal is. Hierdie akkuraatheid is verkry in beide goeie atmosferiese toestande sowel as toestande met rukwinde. Volgens die vlugtoetse blyk dit dat die direkte-lig-bygestaande normaalversnellings beheerder ’n meer akkurate landing kan bewerkstellig as die konvensionele normaal-versnellings beheerder, veral dan in toestande met rukwinde. Die direkte-ligbygestaande normaal-versnellings beheerder het ook ’n laer hei-hoek rotasie tydens die landing vertoon.
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4

Oland, Espen. "Nonlinear Control of Fixed-Wing Unmanned Aerial Vehicles". Doctoral thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for teknisk kybernetikk, 2014. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-27263.

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5

Gaum, Dunross Rudi. "Agressive flight control techniques for a fixed wing unmanned aerial vehicle". Stellenbosch : University of Stellenbosch, 2009. http://hdl.handle.net/10019.1/3112.

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Abstract (sommario):
Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2009.
This thesis investigates aggressive all-attitude flight control systems. These are flight controllers capable of controlling an aircraft at any attitude and will enable the autonomous execution of manoeuvres such as high bank angle turns, steep climbs and aerobatic flight manoeuvres. This class of autopilot could be applied to carry out evasive combat manoeuvres or to create more efficient and realistic target drones. A model for the aircraft’s dynamics is developed in such a way that its high bandwidth specific force and moment model is split from its lower bandwidth kinematic model. This split is done at the aircraft’s specific acceleration and roll rate, which enables the design of simple, decoupled, linear attitude independent inner loop controllers to regulate these states. Two outer loop kinematic controllers are then designed to interface with these inner loop controllers to guide the aircraft through predefined reference trajectories. The first method involves the design of a linear quadratic regulator (LQR) based on the successively linearised kinematics, to optimally control the system. The second method involves specific acceleration matching (SAM) and results in a linear guidance controller that makes use of position based trajectories. These position based trajectories allow the aircraft’s velocity magnitude to be regulated independently of the trajectory tracking. To this end, two velocity regulation algorithms were developed. These involved methods of optimal control, implemented using dynamic programming, and energy analysis to regulate the aircraft’s velocity in a predictive manner and thereby providing significantly improved velocity regulation during aggressive aerobatic type manoeuvres. Hardware in the loop simulations and practical flight test data verify the theoretical results of all controllers presented
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6

Mullen, Jon. "FILTERED-DYNAMIC-INVERSION CONTROL FOR FIXED-WING UNMANNED AERIAL SYSTEMS". UKnowledge, 2014. http://uknowledge.uky.edu/me_etds/45.

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Abstract (sommario):
Instrumented umanned aerial vehicles represent a new way of measuring turbulence in the atmospheric boundary layer. However, autonomous measurements require control methods with disturbance-rejection and altitude command-following capabilities. Filtered dynamic inversion is a control method with desirable disturbance-rejection and command-following properties, and this controller requires limited model information. We implement filtered dynamic inversion as the pitch controller in an altitude-hold autopilot. We design and numerically simulate the continuous-time and discrete-time filtered-dynamic-inversion controllers with anti-windup on a nonlinear aircraft model. Finally, we present results from a flight experiment comparing the filtered-dynamic-inversion controller to a classical proportional-integral controller. The experimental results show that the filtered-dynamic-inversion controller performs better than a proportional-integral controller at certain values of the parameter.
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7

Basson, Matthys Michaelse. "Stall prevention control of fixed-wing unmanned aerial vehicles". Thesis, Stellenbosch : University of Stellenbosch, 2010. http://hdl.handle.net/10019.1/4310.

Testo completo
Abstract (sommario):
Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2010.
ENGLISH ABSTRACT: This thesis presents the development of a stall prevention flight control subsystem, which can easily be integrated into existing flight control architectures of fixed-wing unmanned aerial vehicles (UAV’s). This research forms an important part of faulttolerant flight control systems and will ensure that the aircraft continues to operate safely within its linear aerodynamic region. The focus of this thesis was the stall detection and prevention problem. After a thorough literature study on the topic of stall, a model based stall prevention control algorithm with feedback from an angle of attack sensor was developed. This algorithm takes into account the slew rate and saturation limits of the aircraft’s servos and is able to predict when the current flight condition will result in stall. The primary concern was stall during wings-level flight and involved the prevention of stall by utilising only the elevator control surface. A model predictive slew rate control algorithm was developed to override and dynamically limit the elevator command to ensure that the angle of attack does not exceed a predefined limit. The stall prevention control system was designed to operate as a switching control scheme, to minimise any restrictions imposed on the existing flight control system. Finally, software in the loop simulations were conducted using a nonlinear aircraft model and realistic sensor noise, to verify the theoretical results obtained during the development of this stall prevention control strategy. A worst-case performance analysis was also conducted to investigate the robustness of the control algorithms against model uncertainties.
AFRIKAANSE OPSOMMING: Hierdie tesis handel oor die ontwikkeling van ’n staak voorkomings-vlugbeheer substelsel wat maklik geïntegreer kan word in bestaande vlugbeheer argitektuur van onbemande vaste-vlerk lugvaartuie. Hierdie tesis vorm ’n belangrike deel van fouttolerante vlugbeheertegnieke en sal verseker dat die vliegtuig slegs binne sy lineêre aerodinamiese werksgebied bly. Die fokus van hierdie tesis is die staak opsporing en voorkomings probleem. Na afloop van ’n deeglike literatuurstudie oor die onderwerp van staak, is ’n model gebaseerde staak voorkomings-beheertegniek ontwikkel, wat terugvoer van ’n invalshoek sensor ontvang. Hierdie algoritme neem die sleur tempo en defleksie limiete van die vliegtuig se servos in ag en is in staat om staak te voorspel. Die primêre oorweging was staak tydens simmetriese vlugte en behels slegs die voorkoming van staak deur gebruik te maak van die hei beheer oppervlak. ’n Model voorspellings sleur tempo beheeralgoritme is ontwikkel om die hei-roer dinamies te beperk sodat die invalshoek nie ’n sekere vooraf bepaalde limiet oorskry nie. Die staak voorkomings beheerstelsel is ontwerp om te funksioneer as ’n skakel beheer skema om die beperkings op die bestaande vlugbeheerstelsel te minimaliseer. Laastens was sagteware-in-die-lus simulasies gebruik om die teoretiese resultate, wat verkry is tydens die ontwikkeling van hierdie staak voorkomings beheer-strategie, te kontroleer. Om die robuusthied van hierdie beheeralgoritmes teen model onsekerhede te ondersoek, is ’n ergste-geval prestasie analise ook uitgevoer.
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8

Persson, Linnea. "Cooperative Control for Landing a Fixed-Wing Unmanned Aerial Vehicle on a Ground Vehicle". Thesis, KTH, Skolan för elektro- och systemteknik (EES), 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-187667.

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Abstract (sommario):
High Altitude Long Endurance (HALE) platforms are a type of Unmanned Aerial Vehicle (UAV). With their relatively easy deployment and independence of a fixed orbit, HALE UAVs have the potential to replace satellites for certain tasks in the future. A challenge with this technology is that the current platforms are too heavy to fly for a long period of time. A suggested method for reducing the weight is to remove the landing gear to instead use alternative methods for take-off and landing. One such alternative method is to land the UAV on top of a cooperating ground vehicle. In this thesis, the cooperative controller and the experimental setup of such a landing have been investigated. The cooperation between the systems was analyzed and evaluated analytically, through simulations and with flight tests. Using a PID controller for the position alignment and a modified flare law for the descent, feasibility of the landing was verified by performing a landing of a Penguin BE fixed-wing UAV on top of a cooperating ground vehicle.
Så kallade HALE - High Altitude Long Endurance -farkoster är en växande teknik inom området för autonoma flygplan. Med fördelar som exempelvis en möjlighet att röra sig oberoende av en omloppsbana samt en mer effektiv implementering– och utvecklingsprocess har de visat potential att i framtiden kunna ersätta satelliter inom vissa områden. Ett problem är i dagsläget svårigheten att bygga tillräckligt lätta farkoster för att kunna flyga under en längre tidsperiod. För att minska vikten har det bland annat föreslagits att landningsställ kan tas bort för att istället använda alternativa start- och landningsmetoder. I detta projekt har en metod undersökts där idén är att landa ett autonomt flygplan på en mobil plattform. Samarbetet mellan systemen har analyserats både analytiskt och genom tester. Slutligen verifieras att en kooperativ landning är genomförbar genom att en landning av ett obemannat flygplan på en samarbetande bil utförs.
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9

Smit, Samuel Jacobus Adriaan. "Autonomous landing of a fixed-wing unmanned aerial vehicle using differential GPS". Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/80122.

Testo completo
Abstract (sommario):
Thesis (MScEng)--Stellenbosch University, 2013.
ENGLISH ABSTRACT: This dissertation presents the design and practical demonstration of a flight control system (FCS) that is capable of autonomously landing a fixed-wing, unmanned aerial vehicle (UAV) on a stationary platform aided by a high-precision differential global positioning system. This project forms part of on-going research with the end goal of landing a fixed-wing UAV on a moving platform (for example a ship’s deck) in windy conditions. The main aim of this project is to be able to land the UAV autonomously, safely and accurately on the runway. To this end, an airframe was selected and equipped with an avionics payload. The equipped airframe’s stability derivatives were analysed via AVL and the moment of inertia was determined by the double pendulum method. The aircraft model was developed in such a way that the specific force and moment model (high bandwidth) is split from the point-mass dynamics of the aircraft (low bandwidth) [1]. The advantage of modelling the aircraft according to this unique method, results in a design that has simple decoupled linear controllers. The inner-loop controllers control the high-bandwidth specific accelerations and roll-rate, while the outer-loop controllers control the low-bandwidth point-mass dynamics. The performance of the developed auto-landing flight control system was tested in software-in-the-loop (SIL) and hardware-in-the-loop (HIL) simulations. A Monte Carlo non-linear landing simulation analysis showed that the FCS is expected to land the aircraft 95% of the time within a circle with a diameter of 1.5m. Practical flight tests verified the theoretical results of the developed controllers and the project was concluded with five autonomous landings. The aircraft landed within a circle with a 7.5m radius with the aiming point at the centre of the circle. In the practical landings the longitudinal landing error dominated the landing performance of the autonomous landing system. The large longitudinal error resulted from a climb rate bias on the estimated climb rate and a shallow landing glide slope.
AFRIKAANSE OPSOMMING: Hierdie skripsie stel die ontwikkeling en praktiese demonstrasie van ʼn self-landdende onbemande vastevlerkvliegtuigstelsel voor, wat op ʼn stilstaande platform te lande kan kom met behulp van ʼn uiters akkurate globale posisionering stelsel. Die projek maak deel uit van ʼn groter projek, waarvan die doel is om ʼn onbemande vastevlerkvliegtuig op ʼn bewegende platform te laat land (bv. op ʼn boot se dek) in onstuimige windtoestande. Die hoofdoel van die projek was om die vliegtuig so akkuraat as moontlik op die aanloopbaan te laat land. ʼn Vliegtuigraamwerk is vir dié doel gekies wat met gepaste avionica uitgerus is. Die uitgeruste vliegtuig se aerodinamsie eienskappe was geanaliseer met AVL en die traagheidsmoment is deur die dubbelependulum metode bepaal. Die vliegtuigmodel is op so ‘n manier onwikkel om [1] die spesifieke krag en momentmodel (vinnige reaksie) te skei van die puntmassadinamiek (stadige reaksie). Die voordeel van hierdie wyse van modulering is dat eenvoudige ontkoppelde beheerders ontwerp kon word. Die binnelusbeheerders beheer die vinnige reaksie-spesifieke versnellings en die rol tempo van die vliegtuig. Die buitelusbeheerders beheer die stadige reaksie puntmassa dinamiek. Die vliegbeheerstelsel is in sagteware-in-die-lus en hardeware-in-die-lus simulasies getoets. Die vliegtuig se landingseienskappe is ondersoek deur die uitvoer van Monte Carlo simulasies, die simulasie resultate wys dat die vliegtuig 95% van die tyd binne in ʼn sirkel met ʼn diameter van 1.5m geland het. Praktiese vlugtoetse het bevestig dat die teoretiese uitslae en die prakties uitslae ooreenstem. Die vliegtuig het twee suksesvolle outomatiese landings uitgevoer, waar dit binne ʼn 7.5m-radius sirkel geland het, waarvan die gewenste landingspunt die middelpunt was. In die outomatiese landings is die longitudinale landingsfout die grootse. Die groot longitudinale landingsfout is as gevolg van ʼn afset op die afgeskatte afwaartse spoed en ʼn lae landings gradiënt.
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10

Alatorre, Sevilla Armando. "Landing of a fixed-wing unmanned aerial vehicle in a limited area". Electronic Thesis or Diss., Compiègne, 2024. http://www.theses.fr/2024COMP2801.

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Le projet de thèse consiste à développer une solution pour l'atterrissage d'un drone à voilure fixe de configuration classique dans une zone limitée. Le principal défi consiste à réduire la vitesse de l'avion à une phase minimale pendant le vol, à l'aide d'algorithmes de contrôle automatique. La réduction de la vitesse d'un drone à voilure fixe s'effectue en augmentant son angle d'attaque, ce qui implique un freinage par la force de traînée. Cependant, cette manœuvre est critique pour un avion conventionnel, parce que si son angle d'attaque augmente au-delà de l'angle de décrochage, le véhicule peut perdre sa contrôlabilité, c'est-à-dire qu'il est possible que le véhicule aérien s'effondre et que sa structure soit endommagée. Le modèle mathématique est une représentation d'équations qui décrit le comportement de la dynamique du système. En considérant plusieurs variables pour obtenir une meilleure approximation de la dynamique du système, dans notre cas le véhicule à voilure fixe, la conception des stratégies de contrôle sera plus difficile et plus complexe. Dans ce travail de recherche, nous utiliserons un modèle mathématique non linéaire car les effets de décrochage peuvent être inclus par des approximations mathématiques du moment de tangage, des forces de portance et de traînée. Cela nous permet d'obtenir une meilleure performance des lois de contrôle pour la navigation autonome du drone à voilure fixe. L'une des limites des véhicules à voilure fixe est qu'ils atterrissent dans des espaces de dimensions réduites et que le pourcentage de dommages subis par leur structure est élevé. En outre, les perturbations extérieures et l'inexpérience des pilotes augmentent le risque de dommages. Il est bien connu qu'il est très difficile de satisfaire aux conditions d'une piste d'atterrissage. Par conséquent, la communauté scientifique s'est efforcée de mettre au point des solutions pour l'atterrissage dans des zones limitées. Dans la littérature, on trouve quelques solutions basées sur des véhicules hybrides et des systèmes de récupération. Les véhicules hybrides consistent à modifier la structure d'un véhicule à voilure fixe. Les moteurs sont répartis stratégiquement pour obtenir une configuration de véhicule multirotor, offrant certaines caractéristiques telles que le décollage et l'atterrissage verticaux. Cependant, ces actionneurs augmentent la masse du véhicule, la consommation d'énergie (ce qui réduit la durabilité du vol), la probabilité de défaillance, le coût d'acquisition, de réparation et d'entretien. Notre objectif dans ce travail de recherche est de concevoir et de valider des stratégies de contrôle pour l'atterrissage d'un drone à voilure fixe dans un espace limité. Les stratégies de contrôle ont été conçues selon deux approches : la première est basée sur le développement de manœuvres pour un drone à voilure fixe afin de réduire la vitesse à une phase minimale pendant le vol. Dans la deuxième approche, nous avons travaillé sur les stratégies de contrôle pour l'atterrissage d'un drone à voilure fixe sur un véhicule terrestre en mouvement. Une stratégie de contrôle a été proposée pour réduire la vitesse du drone à voilure fixe au minimum afin d'être capturé par un système de récupération. La stratégie de contrôle a été divisée en trois étapes de vol : dans la première étape, l'avion s'aligne dans le plan x-y tandis qu'il est conduit à une altitude souhaitée pour effectuer un vol de croisière. L'étape suivante consiste en un vol ascendant, axé sur le suivi d'une référence angulaire basée sur une trajectoire phugoïde. Cette trajectoire implique une augmentation de l'angle d'attaque jusqu'à l'angle de décrochage de l'avion. Ainsi, la vitesse aérienne obtient une réduction maximale dans des conditions sûres, permettant au drone d'être capturé par le système de récupération. Toutefois, si le drone n'est pas capturé par le système de récupération, une stratégie de contrôle est appliquée pour rétablir le vol de l'aéronef
The development of this thesis consists of designing some control strategies that allow a fixedwing drone with classical configuration to perform a safe landing in a limited area. The main challenge is to reduce the aircraft’s airspeed avoiding stall conditions. The developed control strategies are focused on two approaches: the first approach consists of the designing airspeed reduction maneuvers for a fixed-wing vehicle to be captured by a recovery system and for a safe landing at a desired coordinate. The next approach is focused on landing a fixed-wing drone on a moving ground vehicle. A dynamic landing trajectory was designed to lead a fixedwing vehicle to the position of a ground vehicle, reaching its position in a defined distance. Moreover, this trajectory was used in a cooperative control design. The control strategy consists of the synchronization of both vehicles to reach the same position at a desired distance. The aerial vehicle tracks the dynamic landing trajectory, and the ground vehicle controls its speed. In addition, we will propose a control architecture with a different focus, where the ground vehicle performs the tracking task of the aerial vehicle’s position in order to be captured. And, the drone’s task is to track a descending flight until the top of the ground vehicle. However, considering the speed difference between both vehicles. Therefore, we propose a new control architecture defining that the aircraft performs an airspeed reduction strategy before beginning its landing stage. The aircraft will navigate to a minimum airspeed, thus, allowing the ground vehicle to reach the fixed-wing drone’s position by increasing its speed. The control laws of each strategy were determined by developing the Lyapunov stability analysis, thus, the stability is guaranteed in each flight stage. Finally, the control strategies were implemented on prototypes allowing us to validate their performance and obtain satisfactory results for safe landing of a fixed-wing drone with classical configuration
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Più fonti

Libri sul tema "Fixed-wing unmanned aerial vehicle"

1

Greer, Daniel S. Avionics System development for a Rotary Wing Unmanned Aerial Vehicle. Monterey, Calif: Naval Postgraduate School, 1998.

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2

Tran, Fleischer Van, e Hugh L. Dryden Flight Research Center, a cura di. Methods for in-flight wing shape predictions of highly flexible unmanned aerial vehicles: Formulation of Ko displacement theory. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2010.

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3

Office, General Accounting. Unmanned aerial vehicles: No more Hunter systems should be bought until problems are fixed : report to the Secretary of Defense. Washington, D.C: The Office, 1995.

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Avionics System Development for a Rotary Wing Unmanned Aerial Vehicle. Storming Media, 1998.

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5

Wich, Serge A., e Lian Pin Koh. Typology and anatomy of drones. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780198787617.003.0002.

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In this chapter we discuss the typology of drones that are currently being used for different kinds of environmental and conservation applications. Drones are also commonly known variously as Remotely Piloted Aircraft Systems (RPAS), Unmanned Aerial Vehicles (UAV), and Unmanned Aircraft Systems (UAS). We focus on the most popular aircraft types including multirotor (of various configurations), fixed wing, and hybrid ‘vertical-take-off-and-landing’ (VTOL) craft, and briefly discuss the relative pros and cons of each type. We also broadly discuss the essential components common to all remotely piloted aircraft systems, including the power source, flight controller (or autopilot), and ground control station.
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Capitoli di libri sul tema "Fixed-wing unmanned aerial vehicle"

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Özbek, Emre, Selcuk Ekici e T. Hikmet Karakoc. "An Evaluation on Landing Gear Configurations of Fixed-Wing, Rotary-Wing, and Hybrid UAVs". In Unmanned Aerial Vehicle Design and Technology, 153–65. Cham: Springer International Publishing, 2023. http://dx.doi.org/10.1007/978-3-031-45321-2_9.

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Dobrokhodov, Vladimir. "Kinematics and Dynamics of Fixed-Wing UAVs". In Handbook of Unmanned Aerial Vehicles, 243–77. Dordrecht: Springer Netherlands, 2014. http://dx.doi.org/10.1007/978-90-481-9707-1_53.

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Yu, Ziquan, Youmin Zhang, Bin Jiang e Chun-Yi Su. "Fixed-Wing UAV Model". In Fault-Tolerant Cooperative Control of Unmanned Aerial Vehicles, 19–24. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-7661-4_2.

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Owen, Mark, Randal W. Beard e Timothy W. McLain. "Implementing Dubins Airplane Paths on Fixed-Wing UAVs*". In Handbook of Unmanned Aerial Vehicles, 1677–701. Dordrecht: Springer Netherlands, 2014. http://dx.doi.org/10.1007/978-90-481-9707-1_120.

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Mills, Steven J., Jason J. Ford e Luis Mejías. "Vision Based Control for Fixed Wing UAVs Inspecting Locally Linear Infrastructure Using Skid-to-Turn Maneuvers". In Unmanned Aerial Vehicles, 29–42. Dordrecht: Springer Netherlands, 2010. http://dx.doi.org/10.1007/978-94-007-1110-5_4.

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Ryaciotaki-Boussalis, Helen, e Darrell Guillaume. "Computational and Experimental Design of a Fixed-Wing UAV". In Handbook of Unmanned Aerial Vehicles, 109–41. Dordrecht: Springer Netherlands, 2014. http://dx.doi.org/10.1007/978-90-481-9707-1_121.

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Kownacki, Cezary, e Daniel Ołdziej. "Flocking Algorithm for Fixed-Wing Unmanned Aerial Vehicles". In Advances in Aerospace Guidance, Navigation and Control, 415–31. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-17518-8_24.

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Agarwal, Varun, e Rajiv Ranjan Tewari. "Delivering Newspapers Using Fixed Wing Unmanned Aerial Vehicles". In Advances in Intelligent Systems and Computing, 615–27. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-6981-8_49.

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Zhong, Gang, Yi Mao, Liandong Zhang, Shangwen Yang e Hao Liu. "Fast Path Planning for Fixed-Wing Unmanned Aerial Vehicle with Multiple Constraints". In Lecture Notes in Electrical Engineering, 101–13. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-5615-7_6.

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Bakirci, Murat, e Muhammed Mirac Ozer. "Adapting Swarm Intelligence to a Fixed Wing Unmanned Combat Aerial Vehicle Platform". In Studies in Big Data, 433–79. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-38325-0_18.

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Atti di convegni sul tema "Fixed-wing unmanned aerial vehicle"

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Tahar, Khairul Nizam, Anuar Ahmad, Wan Abdul Aziz Wan Mohd Akib e Wan Mohd Naim Wan Mohd. "Aerial mapping using autonomous fixed-wing unmanned aerial vehicle". In 2012 IEEE 8th International Colloquium on Signal Processing & its Applications (CSPA). IEEE, 2012. http://dx.doi.org/10.1109/cspa.2012.6194711.

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El Tin, Fares, Inna Sharf e Meyer Nahon. "Fire Monitoring with a Fixed-wing Unmanned Aerial Vehicle". In 2022 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2022. http://dx.doi.org/10.1109/icuas54217.2022.9836074.

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Petrík, Nikolas Michael, e Pavol Pecho. "Design and construction of a UAV device with a fixed wing for the conditions of rescue services". In Práce a štúdie. University of Zilina, 2021. http://dx.doi.org/10.26552/pas.z.2021.2.32.

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The paper is focused on comprehensive design of an unmanned aerial vehicle with fixed wing, which would add efficiency to specific activities performed by rescue services. The current rapid development of unmanned aerial vehicles is slowly becoming part of many industries around the world. The aim of this paper is to design an unmanned aerial vehicle that could provide safe, reliable, and efficient operation. The overall design, construction, and installation of the proposed unmanned aerial vehicle should integrate several modern technologies. To make an ideal design of unmanned aerial vehicle it is required to possess the knowledge of current construction methods of additive manufacturing, understanding of legislation in operating conditions and, in addition to general knowledge of unmanned vehicles, also comprehensive skills in programming and configuration of autonomous control elements of autonomous unmanned systems. After the production of the unmanned aerial vehicle with fixed wing, very good technical properties were demonstrated during experimental ground tests. Achieved technical properties are comparable to those owned by the unmanned aerial vehicles that are currently on the market. The final design configuration using an infrared-sensitive optical device could perform activities such as: searching for missing persons in hard-to-reach and vast terrain or searching for forest fires.
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Raghuwaiya, Krishna, e Roneel Chand. "3D Motion Planning of a Fixed-Wing Unmanned Aerial Vehicle". In 2018 5th Asia-Pacific World Congress on Computer Science and Engineering (APWC on CSE). IEEE, 2018. http://dx.doi.org/10.1109/apwconcse.2018.00046.

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Akbar, Mahesa, Ahmad Riyad Firdaus, Sapto Wibowo e Nanda Wirawan. "Piezoelectric Energy Harvesting from A Fixed-wing Unmanned Aerial Vehicle". In 2019 2nd International Conference on Applied Engineering (ICAE). IEEE, 2019. http://dx.doi.org/10.1109/icae47758.2019.9221651.

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Liang, Chao, e Chenxiao Cai. "Modeling of a rotor/fixed-wing hybrid unmanned aerial vehicle". In 2017 36th Chinese Control Conference (CCC). IEEE, 2017. http://dx.doi.org/10.23919/chicc.2017.8029181.

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Chakraborty, Anusna, Clark N. Taylor, Rajnikant Sharma e Kevin M. Brink. "Cooperative localization for fixed wing unmanned aerial vehicles". In 2016 IEEE/ION Position, Location and Navigation Symposium (PLANS). IEEE, 2016. http://dx.doi.org/10.1109/plans.2016.7479689.

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Gryte, Kristofer, Richard Hann, Mushfiqul Alam, Jan Rohac, Tor Arne Johansen e Thor I. Fossen. "Aerodynamic modeling of the Skywalker X8 Fixed-Wing Unmanned Aerial Vehicle". In 2018 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2018. http://dx.doi.org/10.1109/icuas.2018.8453370.

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Phelps, David, Kanishke Gamagedara, Jeremey Waldron, Kalpesh Patil e Murray Snyder. "Ship Air Wake Detection Using Small Fixed Wing Unmanned Aerial Vehicle". In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0784.

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Levin, Joshua, Aditya Paranjape e Meyer Nahon. "Motion Planning for a Small Aerobatic Fixed-Wing Unmanned Aerial Vehicle". In 2018 IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS). IEEE, 2018. http://dx.doi.org/10.1109/iros.2018.8593670.

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Rapporti di organizzazioni sul tema "Fixed-wing unmanned aerial vehicle"

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Yang, Justin A. Conceptual Aerodynamic Modeling of a Flapping Wing Unmanned Aerial Vehicle. Fort Belvoir, VA: Defense Technical Information Center, novembre 2013. http://dx.doi.org/10.21236/ada592189.

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She, Ruifeng, e Yanfeng Ouyang. Analysis of Drone-based Last-mile Delivery Systems under Aerial Congestion: A Continuum Approximation Approach. Illinois Center for Transportation, agosto 2023. http://dx.doi.org/10.36501/0197-9191/23-014.

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This paper presents a systematic analysis and design framework for a spectrum of last-mile delivery systems that leverage unmanned aerial vehicles (UAVs). Four distinct modes are considered: (1) direct drone deliveries from a fixed depot; (2) drone deliveries from parked trucks that carry bulk parcels to customer neighborhoods; (3) drone deliveries from nonstopping trucks that tour customer neighborhoods; and (4) as a benchmark, traditional truck-based home deliveries. We present a new continuum-approximation approach that is used for analysis of both truck routing and aerial-UAV traffic. We compared the operational cost and efficiency of different delivery schemes to reveal how a certain scheme is the most efficient under various scenarios. We demonstrate the applicability of our model on expansive real-world roadway networks and further conduct analysis on grid networks, yielding key analytical insights. The drone-based delivery is demonstrated to be superior to conventional truck-only delivery, suggesting a significant potential for socioeconomic benefit. It is observed that when servicing a relatively low demand over a small area, dispatching drones directly from the distribution facility is the most efficient method. As the demand grows or spans a wider area, collaborative strategies are preferred, as they better cope with certain aspects, such as the long line-haul cost or the ramping aerial congestion, by striking a balance between efficiency and flexibility.
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Christensen, Lance. PR-459-133750-R03 Fast Accurate Automated System To Find And Quantify Natural Gas Leaks. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), novembre 2019. http://dx.doi.org/10.55274/r0011633.

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Miniature natural gas sensors weighing a few hundred grams with 10 ppb s-1 sensitivity towards methane and ppb s-1 sensitivity towards methane and ethane present the energy industry with cost effective ways to improve safety, comply with State and Federal regulations, decrease natural gas emissions, and attribute natural gas indications to thermogenic or biogenic sources. One particularly promising implementation is on small unmanned aerial systems (sUASs) flown by service providers or in-house personnel or even more ambitiously as part of larger network conducting autonomous, continual monitoring. This report describes refinement of the OPLS measurement system to include all ancillary instruments needed to put OPLS methane and ethane measurements into context for leak surveillance, localization, and quantification. Flights were conducted on a variety of VTOLs and fixed wing drones as described below to ensure that the overall system development resulted in a system that was platform agnostic. This report describes: - The complete agnostic OPLS measurement system.The individual components are described and their performance investigated.Technical issues that arose during testing and field deployment are described. - Field experiments of the refined OPLS measurement system at a real-world oil and gas production site.These experiments exercise the OPLS system's ability to do leak surveillance, localization, and quantification. - Laboratory development of the OPLS instrument to improve its performance in terms of signal-to-noise and accuracy. - Field experiments demonstrating the successful application of OPLS on a fixed-wing hybrid flown at altitudes higher than 50 m. - Field experiments demonstrating the utility of source attribution using the ethane measurement capability. There is a related webinar.
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Price, Donald. SM-403-148100-R01 Mineral Wells 2012 RAM Gas and Oil Leak Detection Field Study Results. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), dicembre 2015. http://dx.doi.org/10.55274/r0010851.

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In June 2012, the RAM Program conducted a comprehensive field study to evaluate the performance of current off the shelf sensor technologies for detecting gas and oil leaks on pipelines. This study had three key objectives: 1. Evaluate the capabilities of current technologies that are offered commercially for methane leak detection monitoring using standard pipeline patrol aircraft 2. Provide a test location for development of emerging technologies that are not yet commercially available for pipeline leak detection 3. Assess the feasibility of using airborne sensors to detect staged liquid oil leaks The field study was conducted on two of Enbridge�s operating pipelines located near Mineral Wells, Texas. This location provided realistic conditions for assessing the capabilities and limitations of automated sensor systems that are currently available for leak detection. Three airborne leak detection vendors (Lasen, Pergam, and New Era Technology), and one ground vehicle vendor (Picarro), completed the field study. The field study was performed as part of the 2012 PRCI RAM program that is primarily focused on leak detection technologies using aerial platforms. The study tested a range of sensors designed for gas leak detection using systems mounted on helicopters and fixed wing aircraft. Enbridge staged a series of controlled gas releases simulating pipeline gas leaks. Qualified operators released a series of prescribed natural gas leaks from 8 known locations along the pipelines in order to simulate transmission leaks of varying sizes. Additionally, Enbridge placed 8 liquid petroleum targets along the test pipelines. These gas and oil targets allowed for a direct comparison of technology performance against a known set of conditions. Standard leak patrol methods (ground survey with foot patrol) were also used to identify any emission sources other than the controlled releases. The results from the field study show that 3 of the 4 vendor sensor technologies tested are now feasible alternatives for gas leak detection. The findings for liquid leak detection were promising, but inconclusive due to plume overlaps between gas and oil targets. The sensors used by the vendors in this field test were optimized for detecting methane gas and not oil vapors. Therefore, until additional studies are performed on liquid hydrocarbon volatilization, it is premature to conclude that the tested technologies are or are not appropriate for oil leak detection.
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