Academic literature on the topic 'Fixed-wing drone'
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Journal articles on the topic "Fixed-wing drone"
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Suroso, Indreswari, and Erwhin Irmawan. "Analysis Of Aerial Photography With Drone Type Fixed Wing In Kotabaru, Lampung." Journal of Applied Geospatial Information 2, no. 1 (May 4, 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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Suroso, Indreswari. "ANALISIS PERAN UNMANNED AERIAL VEHICLE JENIS MULTICOPTER DALAM MENINGKATKAN KUALITAS DUNIA FOTOGRAFI UDARA DI LOKASI JALUR SELATAN MENUJU CALON BANDARA BARU DI KULONPROGO." REKAM: Jurnal Fotografi, Televisi, dan Animasi 14, no. 1 (August 15, 2018): 17. http://dx.doi.org/10.24821/rekam.v14i1.2134.
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Dunia fotografi sangat erat berkaitan dengan pesawat tanpa awat disebut drone. Drone dipasang kamera sehingga pesawat tersebut dikendalikan pilot dari daratan. Hasil fotografi dilihat pilot setelah pesawat drone tersebut mendarat. Drone adalah pesawat tanpa awak yang dikendalikan dari jarak jauh. Pesawat tanpa awak atau pesawat nirawak (Unmanned Aerial Vehicle atau UAV) adalah sebuah mesin terbang yang berfungsi dengan kendali jarak jauh oleh pilot. Perkembangan teknologi membuat drone juga mulai banyak diterapkan untuk kebutuhan sipil, terutama di bidang bisnis, industri, dan logistik. Dalam dunia industri bisnis, drone telah diterapkan dalam berbagai layanan seperti pengawasan infrastruktur, pengiriman paket barang, pemadam kebakaran hutan, eksplorasi bahan tambang, pemetaaan daerah pertanian, dan pemetaan daerah industri. Berdasarkan jenisnya, terdapat dua jenis drone, yaitu multicopter dan fixed wing. Multicopter adalah jenis drone yang memanfaatkan putaran baling-baling untuk terbang, sedangkan fixed wing memiliki bentuk seperti pesawat terbang biasa yang dilengkapi sistem sayap. Langkah yang digunakan dalam penelitian ini adalah persiapan pembuatan drone, perencanaan ketinggian terbang, pengujian drone di ground, pengaturankalibrasi kamera, pengambilan foto udara, melihat hasil foto udara, kemudian menganalisis hasil foto udara. Drone dalam penelitian ini memiliki empat propeller, yang digunakan untuk pemetaan jalur selatan menuju pintu masuk New International Yogyakarta Airports melalui Desa Plumbon, Kecamatan Temon, Kabupaten Kulonprogo. AbstractRole Analysis of Unmanned Aerial Vehicle Type MultiCopter in Improving the Quality of Aerial Photography Field in the Southern Path towards the Prospective New Airport in Kulonprogo. The world of photography is very closely related to the unattended aircraft called drones. Drones are mounted with camera so that the plane is pilot-controlled from the mainland. Photography results are seen by the pilot after the drone aircraft is landed. Drones are unmanned aircraft controlled remotely. Unmanned aircraft or Unmanned Aerial Vehicle (UAV), is a flying machine which is operated with remote control by the pilot. Technological developments make the drones also start widely applied to civilian needs, especially in the areas of business, industry and logistics. In business industry, drones have been applied in various services such as infrastructure monitoring, freight forwarding, forest fire-fighter, mining exploration, agricultural mapping, and industrial area mapping. Based on its type, there are two types of drones, namely multicopter and fixed wing. Multicopter is the type of drone that utilizes the spin of the propeller, while the fixed wing has an airplane-like shape with a wing system. The steps used in this study were as follows: drone making preparation, fly height planning, ground drone testing, camera calibration settings, air photo capture, air results viewing, and aerial photographs results analyzing. Drone used in this study has fourpropellers used for mapping south path entrance of New Yogyakarta International Airport through Plumbon Village,Temon sub-district, Kulonprogo regency.
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Okulski, Michał, and Maciej Ławryńczuk. "A Small UAV Optimized for Efficient Long-Range and VTOL Missions: An Experimental Tandem-Wing Quadplane Drone." Applied Sciences 12, no. 14 (July 13, 2022): 7059. http://dx.doi.org/10.3390/app12147059.
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Most types of Unmanned Aerial Vehicle (UAV, drone) missions requiring Vertical-Take-Off-and-Landing (VTOL) capability could benefit if a drone’s effective range could be extended. Example missions include Search-And-Rescue (SAR) operations, a remote inspection of distant objects, or parcel delivery. There are numerous research works on multi-rotor drones (e.g., quadcopters), fixed-wing drones, VTOL quadplanes, or tilt-motor/tilt-wing VTOLs. We propose a unique compact VTOL UAV optimized for long hover and long-range missions with great lifting capacity and manoeuvrability: a tandem-wing quadplane with fixed motors only. To the best of our knowledge, such a drone has not yet been researched. The drone was designed, built, and tested in flight. Construction details, its advantages, and issues are discussed in this research.
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Hu, Jiahao, Jingbo Wei, Kun Liu, Xiaobin Yu, Mingzhi Cao, and Zijie Qin. "Hybrid Mode: Routinization of the Transition Mode as the Third Common Mode for Compound VTOL Drones." Drones 8, no. 3 (March 8, 2024): 93. http://dx.doi.org/10.3390/drones8030093.
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Fixed-wing Vertical Takeoff and Landing (VTOL) drones have been widely researched and applied because they combine the advantages of both rotorcraft and fixed-wing drones. However, the research on the transition mode of this type of drone has mainly focused on completing the process quickly and stably, and the application potential of this mode has not been given much attention. The objective of this paper is to routinize the transition mode of compound VTOL drones, i.e., this mode works continuously for a longer period of time as a third commonly used mode besides multi-rotor and fixed-wing modes, which is referred to as the hybrid mode. For this purpose, we perform detailed dynamics modeling of the drone in this mode and use saturated PID controllers to control the altitude, velocity, and attitude of the drone. In addition, for more stable altitude control in hybrid mode, we identify the relevant parameters for the lift of the fixed-wings and the thrust of the actuators. Simulation and experimental results show that the designed control method can effectively control the compound VTOL drone in hybrid mode. Moreover, it is proven that flight in hybrid mode can reduce the flight energy consumption to some extent.
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Alhammadi, Mohamed, Mohammed Alavi, Ali Alameri, and Sharul Sham Bin Dol. "Aerodynamic Study and Design of Fixed Wing and Multi-copter Combination." Engineering World 4 (December 31, 2022): 91–95. http://dx.doi.org/10.37394/232025.2022.4.12.
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This project aims to design a hybrid drone with fixed wing for the stable cruising as well as multi-copters for the vertical take-off and landing (VTOL) operations. Drones are utilized for number of applications leading from transportation to the surveillance purposes. Some drones are popular for their stable operation, while other for optimum landing and takeoff. Therefore, numerical analysis was performed on propeller, landing gear as well as on whole structure of the drone. The observed result from CFD analysis show that the velocity distribution had maximum velocity of 40 m/s at the mid span of the drone. In addition, the maximum stress obtained was on the landing gear with approximate value of 185 MPa which is due to the weigh and payload of the drone. The final model was built after the analytical and numerical analysis in order to achieve sustainable and reliable prototype.
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Yan, Jun, Huiping Hu, Jiangkun Gong, Deyong Kong, and Deren Li. "Exploring Radar Micro-Doppler Signatures for Recognition of Drone Types." Drones 7, no. 4 (April 21, 2023): 280. http://dx.doi.org/10.3390/drones7040280.
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In this study, we examine the use of micro-Doppler signals produced by different blades (i.e., puller and lifting blades) to aid in radar-based target recognition of small drones. We categorize small drones into three types based on their blade types: fixed-wing drones with only puller blades, multi-rotor drones with only lifting blades, and hybrid vertical take-off and landing (VTOL) fixed-wing drones with both lifting and puller blades. We quantify the radar signatures of the three drones using statistical measures, such as signal-to-noise ratio (SNR), signal-to-clutter ratio (SCR), Doppler speed, Doppler frequency difference (DFD), and Doppler magnitude ratio (DMR). Our findings show that the micro-Doppler signals of lifting blades in all three drone types were stronger than those of puller blades. Specifically, the DFD and DMR values of pusher blades were below 100 Hz and 0.3, respectively, which were much smaller than the 200 Hz and 0.8 values for lifting blades. The micro-Doppler signals of the puller blades were weaker and more stable than those of the lifting blades. Our study demonstrates the potential of using micro-Doppler signatures modulated by different blades for improving drone detection and the identification of drone types by drone detection radar.
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Ellis-Felege, Susan N., Tanner Stechmann, Samuel Hervey, Christopher J. Felege, Robert F. Rockwell, and Andrew F. Barnas. "Nesting Common Eiders (Somateria mollissima) show little behavioral response to fixed-wing drone surveys." Drone Systems and Applications 10, no. 1 (January 1, 2022): 1–14. http://dx.doi.org/10.1139/juvs-2021-0012.
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Drones may be valuable in polar research because they can minimize researcher activity and overcome logistical, financial, and safety obstacles associated with wildlife research in polar regions. Because polar species may be particularly sensitive to disturbance and some research suggests behavioral responses to drones are species-specific, there is a need for focal species-specific disturbance assessments. We evaluated behavioral responses of nesting Common Eiders (Somateria mollissima (Linnaeus, 1758), n = 19 incubating females) to first, second, or in a few cases third exposure of fixed-wing drone surveys using nest cameras. We found no effect of drone flights (F[1,23] = 0, P = 1.0) or previous exposures (F[1,23] = 0.75, P = 0.397) on the probability of a daily recess event (bird leaves nests). Drone flights did not impact recess length (F[1,25] = 1.34, P = 0.26); however, Common Eiders with prior drone exposure took longer recess events (F[1,25] = 5.27, P = 0.03). We did not observe any overhead vigilance behaviors common in other species while the drone was in the air, which may reflect Common Eiders’ anti-predator strategies of reducing activity at nests in response to aerial predators. Surveying nesting Common Eider colonies with a fixed-wing drone did not result in biologically meaningful behavioral changes, providing a potential tool for research and monitoring this polar nesting species.
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Huang, Chenn-Jung, Kai-Wen Hu, Hao-Wen Cheng, and Yi-Sin Sie Lin. "A Mission-Oriented Flight Path and Charging Mechanism for Internet of Drones." Sensors 23, no. 9 (April 25, 2023): 4269. http://dx.doi.org/10.3390/s23094269.
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In addition to traditional battery exchange services and stationary charging stations, researchers have proposed wireless charging technology, such as decentralized laser charging or drone-to-drone charging in flight, to provide power to drones with insufficient battery electricity. However, the charging methods presented in the literature will inevitably cause drones to wait in line for charging during peak hours and disrupt their scheduled trips when the number of drones grows rapidly in the future. To the best of our knowledge, there have been no integrated solutions for drone flight path and charging planning to alleviate charging congestion, taking into account the different mission characteristics of drones and the charging cost considerations of drone operators. Accordingly, this paper provides adaptive charging options to help drone operators to solve the above-mentioned problems. Drones on ordinary missions can use conventional battery swap services, wired charging stations, or electromagnetic wireless charging stations to recharge their batteries as usual, whereas drones on time-critical missions can choose drone-to-drone wireless charging or decentralized laser charging deployed along the fight paths to charge the batteries of drones in flight. Notably, since fixed-wing drones have larger wing areas to install solar panels, they can also use solar energy to charge during flight if the weather is clear. The simulation results exhibited that the proposed work reduced the power load of the power grid during peak hours, met the charging needs of each individual drone during flight, and cut down the charging costs of drone operators. As a result, an all-win situation for drone operators, drone customers, and power grid operators was achieved.
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Kapoulas, Ioannis K., Antonios Hatziefremidis, A. K. Baldoukas, Evangelos S. Valamontes, and J. C. Statharas. "Small Fixed-Wing UAV Radar Cross-Section Signature Investigation and Detection and Classification of Distance Estimation Using Realistic Parameters of a Commercial Anti-Drone System." Drones 7, no. 1 (January 6, 2023): 39. http://dx.doi.org/10.3390/drones7010039.
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Various types of small drones constitute a modern threat for infrastructure and hardware, as well as for humans; thus, special-purpose radar has been developed in the last years in order to identify such drones. When studying the radar signatures, we observed that the majority of the scientific studies refer to multirotor aerial vehicles; there is a significant gap regarding small, fixed-wing Unmanned Aerial Vehicles (UAVs). Driven by the security principle, we conducted a series of Radar Cross Section (RCS) simulations on the Euclid fixed-wing UAV, which has a wingspan of 2 m and is being developed by our University. The purpose of this study is to partially fill the gap that exists regarding the RCS signatures and identification distances of fixed-wing UAVs of the same wingspan as the Euclid. The software used for the simulations was POFACETS (v.4.1). Two different scenarios were carried out. In scenario A, the RCS of the Euclid fixed-wing UAV, with a 2 m wingspan, was analytically studied. Robin radar systems’ Elvira Anti Drone System is the simulated radar, operating at 8.7 to 9.65 GHz; θ angle is set at 85° for this scenario. Scenario B studies the Euclid RCS within the broader 3 to 16 Ghz spectrum at the same θ = 85° angle. The results indicated that the Euclid UAV presents a mean RCS value (σ ¯) of −17.62 dBsm for scenario A, and a mean RCS value (σ ¯) of −22.77 dBsm for scenario B. These values are much smaller than the values of a typical commercial quadcopter, such as DJI Inspire 1, which presents −9.75 dBsm and −13.92 dBsm for the same exact scenarios, respectively. As calculated in the study, the Euclid UAV can penetrate up to a distance of 1784 m close to the Elvira Anti Drone System, while the DJI Inspire 1 will be detected at 2768 m. This finding is of great importance, as the obviously larger fixed-wing Euclid UAV will be detected about one kilometer closer to the anti-drone system.
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MARIN, Florin Bogdan, Daniela Laura BURUIANA, Viorica GHISMAN, and Mihaela MARIN. "Deep neural network modeling for CFD simulation of drone bioinspired morphing wings." INCAS BULLETIN 15, no. 4 (December 2, 2023): 149–57. http://dx.doi.org/10.13111/2066-8201.2023.15.4.12.
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In this paper we present a deep neural network modelling using Computational Fluid Dynamics (CFD) simulations data in order to optimize control of bioinspired morphing wings of a drone. Drones flight needs to consider variation in aerodynamic conditions that cannot all be optimized using a fixed aerodynamic profile. Nature solves this issue as birds are changing continuously the shape of their wings depending of the aerodynamic current requirements. One important issue for fixed wing drone is the landing as it is unable to control and most of the time consequences are some damages at the nose. An optimized shape of the wing at landing will avoid this situation. Another issue is that wings with a maximum surface are sensitive to stronger head winds; while wings with a small surface allowing the drone to fly faster. A wing with a morphing surface could adapt its aerial surface to optimize aerodynamic performance to specific flight situations. A morphing wing needs to be controlled in an optimized manner taking into account current aerodynamics parameters. Predicting optimized positions of the wing needs to consider (CFD) prior simulation parameters. The scenarios for flight require an important number of CFD simulation to address different conditions and geometric shapes. We compare in this paper neural network architecture suitable to predict wing shape according to current conditions. Deep neural network (DNN) is trained using data resulted out of CFD simulations to estimate flight conditions.
Dissertations / Theses on the topic "Fixed-wing drone"
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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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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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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.
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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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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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De, Hart Ruan Dirk. "Advanced take-off and flight control algorithms for fixed wing unmanned aerial vehicles." Thesis, Stellenbosch : University of Stellenbosch, 2010. http://hdl.handle.net/10019.1/4179.
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Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2010.ENGLISH ABSTRACT: This thesis presents the development and implementation of a position based kinematic guidance system, the derivation and testing of a Dynamic Pursuit Navigation algorithm and a thorough analysis of an aircraft’s runway interactions, which is used to implement automated take-off of a fixed wing UAV. The analysis of the runway is focussed on the aircraft’s lateral modes. Undercarriage and aerodynamic effects are first analysed individually, after which the combined system is analysed. The various types of feedback control are investigated and the best solution suggested. Supporting controllers are designed and combined to successfully implement autonomous take-off, with acceleration based guidance. A computationally efficient position based kinematic guidance architecture is designed and implemented that allows a large percentage of the flight envelope to be utilised. An airspeed controller that allows for aggressive flight is designed and implemented by applying Feedback Linearisation techniques. A Dynamic Pursuit Navigation algorithm is derived that allows following of a moving ground based object at a constant distance (radius). This algorithm is implemented and verified through non-linear simulation.
AFRIKAANSE OPSOMMING: Hierdie tesis handel oor die ontwikkeling en toepassing van posisie-afhanklike, kinematiese leidings-algoritmes, die ontwikkeling van ’n Dinamiese Volgings-navigasie-algoritme en ’n deeglike analise van die interaksie van ’n lugraam met ’n aanloopbaan sodat outonome opstygprosedure van ’n vastevlerk vliegtuig bewerkstellig kan word. Die bogenoemde analise het gefokus op die laterale modus van ’n vastevlerk vliegtuig en is tweeledig behartig. Die eerste gedeelte het gefokus op die analise van die onderstel, terwyl die lugraam en die aerodinamiese effekte in die tweede gedeelte ondersoek is. Verskillende tipes terugvoerbeheer vir die outonome opstygprosedure is ondersoek om die mees geskikte tegniek te bepaal. Addisionele beheerders, wat deur die versnellingsbeheer gebaseerde opstygprosedure benodig word, is ontwerp. ’n Posisie gebaseerde kinematiese leidingsbeheerstruktuur om ’n groot persentasie van die vlugvermoë te benut, is ontwikkel. Terugvoer linearisering is toegepas om ’n lugspoedbeheerder , wat in staat is tot aggressiewe vlug, te ontwerp. ’n Dinamiese Volgingsnavigasie-algoritme wat in staat is om ’n bewegende grondvoorwerp te volg, is ontwikkel. Hierdie algoritme is geïmplementeer en bevestig deur nie-lineêre simulasie.
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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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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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Redding, Joshua D. "Vision-based Target Localization from a Small, Fixed-wing Unmanned Air Vehicle." Diss., CLICK HERE for online access, 2005. http://contentdm.lib.byu.edu/ETD/image/etd895.pdf.
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Lugo, Cárdenas Israel. "Autonomous take-off and landing for a fixed wing UAV." Thesis, Compiègne, 2017. http://www.theses.fr/2017COMP2364/document.
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Ce travail étudie certains des problèmes les plus pertinents dans le sens de la navigation et contrôle présentés dans une classe particulière de mini-véhicules aériens. L'un des principaux objectifs c'est à réaliser un véhicule léger et facile à déployer dans un court laps de temps, un véhicule sans pilote drone capable de suivre une mission complète, du décollage aux points de cheminement suivants et de terminer la mission avec un atterrissage autonome à l'intérieur d'une zone délimitée en utilisant une interface graphique dans un ordinateur ou une tablette. La génération de trajectoire II est la partie qui dit le drone où il doit voyager et sont générés par un algorithme intégré sur le drone. Le résultat classique de Dubins est utilisé comme base pour la génération de trajectoire en 2D et nous avons étendu à la génération de trajectoire 3D. Une stratégie de suivi de trajectoire développée en utilisant l'approche de Lyapunov, est présentée pour piloter un drone à voilure fixe à travers tout le chemin désiré. Le concept clé derrière le contrôleur de suivi de trajectoire s'appuie sur la réduction de la distance entre le centre de masse de l'avion p et le point sur la trajectoire q à zéro, ainsi que l'angle entre le vecteur vitesse et la tangente à la trajectoire. Afin de tester les techniques mises au point au cours de la thèse une application C# -Net personnalisée a été développé nommé MAV3DSim (Multi-Aerial Vehicle 3D Simulator). Le MAV3DSim permet une opération de lecture/écriture de/vers le moteur de simulation à partir de laquelle nous pourrions recevoir toutes les informations de capteurs émulés et envoyés par le simulateur. Le système complet est capable d'effectuer un décollage et d'atterrissage autonome, à travers des points de suivi. Ceci est accompli en utilisant chacune des stratégies développées au cours de la thèse. Nous avons une stratégie pour le décollage et l'atterrissage, ce qui est généré par la partie de navigation qui est le générateur de trajectoire. Une fois que nous avons généré le chemin, il est utilisé par la stratégie de suivi de trajectoire et avec ce que nous avons l'atterrissage et le décollage autonomeThis work studies some of the most relevant problems in the direction of navigation and control presented in a particular class of mini‐aircraft. One of the main objectives is to build a lightweight and easy to deploy vehicle in a short period of time, an unmanned aerial vehicle capable of following a complete mission from take‐o⁄ to the following waypoints and complete the mission with an autonomous landing within a delimitated area using a graphical interface in a computer. The Trajectory Generation It is the part that tells the drone where it must travel and are generated by an algorithm built into the drone. The classic result of Dubins is used as a basis for the trajectory generation in 2D and we have extended it to the 3D trajectory generation. A path following strategy developed using the Lyapunov approach is presented to pilot a fixed wing drone across the desired path. The key concept behind the tracking controller is the reduction of the distance between the center of mass of the aircraft p and the point q on the path to zero, as well as the angle between the velocity vector and the vector tangent to the path. In order to test the techniques developed during the thesis a customized C # .Net application was developed called MAV3DSim (Multi‐Aerial Vehicle 3D Simulator). The MAV3DSim allows a read / write operation from / to the simulation engine from which we could receive all emulated sensor information and sent to the simulator. The MAV3DSim consists of three main elements, the simulation engine, the computation of the control law and the visualization interface. The simulation engine is in charge of the numeric integration of the dynamic equations of the vehicle, we can choose between a quadrotor and a xed wing drone for use in simulation. The visualization interface resembles a ground station type of application, where all variables of the vehicle s state vector can be represented on the same screen. The experimental platform functions as a test bed for the control law prototyping. The platform consists of a xed wing aircraft with a PX4 which has the autopilot function as well as a Raspberry PI mini‐computer which to the implementation of the generation and trajectory tracking. The complete system is capable of performing an autonomous take‐o⁄and landing, through waypoints. This is accomplished by using each of the strategies developed during the thesis. We have a strategy for take‐o⁄ and landing, which is generated by the navigationon part that is the trajectory generator. Once we have generated the path, it is used by the trajectory tracking strategy and withthat we have landing and take‐o⁄ autonomously
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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.
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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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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'aéronefThe 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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Puttige, Vishwas Ramadas Engineering & Information Technology Australian Defence Force Academy UNSW. "Neural network based adaptive control for autonomous flight of fixed wing unmanned aerial vehicles." Awarded by:University of New South Wales - Australian Defence Force Academy. Engineering & Information Technology, 2009. http://handle.unsw.edu.au/1959.4/43736.
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This thesis presents the development of small, inexpensive unmanned aerial vehicles (UAVs) to achieve autonomous fight. Fixed wing hobby model planes are modified and instrumented to form experimental platforms. Different sensors employed to collect the flight data are discussed along with their calibrations. The time constant and delay for the servo-actuators for the platform are estimated. Two different data collection and processing units based on micro-controller and PC104 architectures are developed and discussed. These units are also used to program the identification and control algorithms. Flight control of fixed wing UAVs is a challenging task due to the coupled, time-varying, nonlinear dynamic behaviour. One of the possible alternatives for the flight control system is to use the intelligent adaptive control techniques that provide online learning capability to cope with varying dynamics and disturbances. Neural network based indirect adaptive control strategy is applied for the current work. The two main components of the adaptive control technique are the identification block and the control block. Identification provides a mathematical model for the controller to adapt to varying dynamics. Neural network based identification provides a black-box identification technique wherein a suitable network provides prediction capability based upon the past inputs and outputs. Auto-regressive neural networks are employed for this to ensure good retention capabilities for the model that uses the past outputs and inputs along with the present inputs. Online and offline identification of UAV platforms are discussed based upon the flight data. Suitable modifications to the Levenberg-Marquardt training algorithm for online training are proposed. The effect of varying the different network parameters on the performance of the network are numerically tested out. A new performance index is proposed that is shown to improve the accuracy of prediction and also reduces the training time for these networks. The identification algorithms are validated both numerically and flight tested. A hardware-in-loop simulation system has been developed to test the identification and control algorithms before flight testing to identify the problems in real time implementation on the UAVs. This is developed to keep the validation process simple and a graphical user interface is provided to visualise the UAV flight during simulations. A dual neural network controller is proposed as the adaptive controller based upon the identification models. This has two neural networks collated together. One of the neural networks is trained online to adapt to changes in the dynamics. Two feedback loops are provided as part of the overall structure that is seen to improve the accuracy. Proofs for stability analysis in the form of convergence of the identifier and controller networks based on Lyapunov's technique are presented. In this analysis suitable bounds on the rate of learning for the networks are imposed. Numerical results are presented to validate the adaptive controller for single-input single-output as well as multi-input multi-output subsystems of the UAV. Real time validation results and various flight test results confirm the feasibility of the proposed adaptive technique as a reliable tool to achieve autonomous flight. The comparison of the proposed technique with a baseline gain scheduled controller both in numerical simulations as well as test flights bring out the salient adaptive feature of the proposed technique to the time-varying, nonlinear dynamics of the UAV platforms under different flying conditions.
Books on the topic "Fixed-wing drone"
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Sóbester, András, Andrew J. Keane, and James P. Scanlan. Small Unmanned Fixed-Wing Aircraft Design: A Practical Approach. Wiley & Sons, Incorporated, John, 2017.
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Small Unmanned Fixed-wing Aircraft Design: A Practical Approach. Wiley, 2017.
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Sóbester, András, Andrew J. Keane, and James P. Scanlan. Small Unmanned Fixed-Wing Aircraft Design: A Practical Approach. Wiley & Sons, Incorporated, John, 2017.
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Sóbester, András, Andrew J. Keane, and James P. Scanlan. Small Unmanned Fixed-Wing Aircraft Design: A Practical Approach. Wiley & Sons, Limited, John, 2017.
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(Editor), Thomas J. Mueller, and American Institute of Aeronautics and Astronautics (Corporate Author), eds. Fixed and Flapping Wing Aerodynamics for Micro Air Vehicle Applications (Progress in Astronautics and Aeronautics). AIAA (American Institute of Aeronautics & Ast, 2002.
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Wich, Serge A., and 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.
Book chapters on the topic "Fixed-wing drone"
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Rice, Devyn, Samah Ben Ayed, Stephen Johnstone, and Abdessattar Abdelkefi. "Enhancement of Fixed-Wing Space Drone Performance Through Thermoelectric Power Generation." In Lecture Notes in Mechanical Engineering, 194–99. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-52071-7_27.
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Raza, Aamir, Muhammad Safdar, Muhammad Adnan Shahid, Fahd Rasul, and Rehan Mehmood Sabir. "Applications of Drones in High-Tech Agriculture." In Advances in Environmental Engineering and Green Technologies, 88–108. IGI Global, 2023. http://dx.doi.org/10.4018/978-1-6684-9231-4.ch005.
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Drones, also known as unmanned aerial vehicles (UAVs), have revolutionized agriculture by providing efficient, cost-effective, and accurate solutions to traditional farming practices. This chapter provides an overview of the latest drone technologies and their applications in high-tech agriculture/precision agriculture. It explores the various types of drones used in agriculture, such as fixed-wing, rotary-wing, and hybrid drones, and their respective advantages and disadvantages. It also highlights the role of drones in precision agriculture by providing high-resolution real-time data, enabling farmers to make informed decisions regarding crop management and yield optimization. Looking towards the future, the chapter outlines the potential of drone applications for agriculture and discusses the status of drone applications. In conclusion, this chapter highlights the transformative impact of drones on high-tech agriculture, leading to increased efficiency, improved yield predictions, and enhanced resource management.
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Waqas, Muhammad Mohsin, Sikandar Ali, Muthmainnah Muthmainnah, Muhammad Ahmad Rustam, and Alex Khang. "Unmanned Aerial Vehicles (UAVs) in Modern Agriculture." In Advances in Environmental Engineering and Green Technologies, 109–30. IGI Global, 2023. http://dx.doi.org/10.4018/978-1-6684-9231-4.ch006.
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This chapter presents an overview of different types of drones, including fixed-wing, multi-rotor, and hybrid models, discussing their distinct capabilities and advantages for agricultural tasks, and highlighting their potential benefits in agriculture. The chapter then delves into the specific applications of drones in agriculture, focusing on crop health monitoring, soil surveying, water management, spraying, and pest control. It emphasizes the role of drones equipped with advanced sensors and imaging technologies in providing real-time data on crop conditions, enabling farmers to make informed decisions regarding irrigation, fertilization, and pest control strategies. Furthermore, the chapter examines the future prospects of drones in agriculture. It explores ongoing research and development efforts aimed at enhancing drone capabilities. The potential integration of artificial intelligence and machine learning algorithms for processing drone-collected data and generating actionable insights is discussed.
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Collaro, Carolina, and Martin Herkommer. "Research, Application, and Innovation of LiDAR Technology in Spatial Archeology." In Encyclopedia of Information Science and Technology, Sixth Edition, 1–33. IGI Global, 2024. http://dx.doi.org/10.4018/978-1-6684-7366-5.ch054.
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Two universities, the University of Jaén, Spain and the University of San Carlos, Guatemala, in partnership with Quantum Systems GmbH, a German company, conducted an expedition to the Maya Tropical Forest in the Yaxhà-Nakum-Naranjo National Park of El Petén (El Triangulo Cultural), Guatemala, using LiDAR technology. The article takes its cue from the description of this case study and focuses on the application of LiDAR technology to fixed-wing VTOL drones beyond the pilot's line of sight. The context presents significant challenges due to the impenetrability and vegetation of the forest, which protects Maya archaeology but is also a major degradation factor. The authors analyzed the benefits and challenges of using LiDAR for spatial archaeology and concerning the new frontiers of digitization.
Conference papers on the topic "Fixed-wing drone"
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Seewald, Adam, Hector Garcia De Marina, Henrik Skov Midtiby, and Ulrik Pagh Schultz. "Mechanical and Computational Energy Estimation of a Fixed-Wing Drone." In 2020 Fourth IEEE International Conference on Robotic Computing (IRC). IEEE, 2020. http://dx.doi.org/10.1109/irc.2020.00028.
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Safi'i, Imam, Achmad C. Asyary, and Ony Arifianto. "Transition flight simulation of a hybrid VTOL fixed-wing drone." In NATIONAL CONFERENCE ON PHYSICS AND CHEMISTRY OF MATERIALS: NCPCM2020. AIP Publishing, 2021. http://dx.doi.org/10.1063/5.0061425.
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Suroso, Indreswari. "Peran Drone/Unmanned Aerial Vehicle (UAV) Buatan STTKD dalam Dunia Penerbangan." In Seminar Nasional Kebijakan Penerbangan dan Antariksa I. Bogor: In Media, 2017. http://dx.doi.org/10.30536/p.sinaskpa.i.12.
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Drone adalah pesawat tanpa awak yang dikendalikan dari jarak jauh. Pesawat tanpa awak atau Pesawat nirawak (Unmanned Aerial Vehicle atau UAV), adalah sebuah mesin terbang yang berfungsi dengan kendali jarak jauh oleh pilot atau mampu mengendalikan dirinya sendiri, menggunakan hukum aerodinamika untuk mengangkat dirinya, bisa digunakan kembali dan mampu membawa muatan baik senjata maupun muatan lainnya. Perkembangan teknologi membuat drone juga mulai banyak diterapkan untuk kebutuhan sipil, terutama di bidang bisnis, industri dan logistik. Dunia industri bisnis, drone telah diterapkan dalam berbagai layanan seperti pengawasan Infrastruktur, pengiriman paket barang, pemadam kebakaran hutan, eksplorasi bahan tambang, pemetaan daerah pertanian, dan pemetaan daerah industri. Berdasarkan jenisnya, terdapat dua jenis drone, yaitu multicopter dan fixed wing. Fixed wing memiliki bentuk seperti pesawat terbang biasa yang dilengkapi sistem sayap. Tipe fixed-wing memerlukan desain aerodinamika pada sayap dan badannya sehingga perancangannya cukup rumit. Multicopter yaitu jenis drone yang memanfaatkan putaran baling-baling untuk terbang. Drone Sekolah Tinggi Teknologi Kedirgantaraan (STTKD) memiliki jenis multicopter, dan sudah dipergunakan untuk pemetaan di wilayah Kulonprogo terletak di Desa Glagah Temon dekat runway calon bandara dengan waktu operasional Drone STTKD kurang lebih 20 menit dan beban yang dapat diangkat 1 kg.
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Bluman, James, Davonte Carter Vault, Wei Kang Soon, Ruth Talbott, Jonathan Willis, Andrew Kopeikin, and Ekaterina Prosser. "Autonomous Drone Delivery From Airdrop Systems (ADDAS): Aerially Deploying Folding-Wing Drones for Ground Reconnaissance." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-24046.
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Abstract Extending the long-range capabilities of unmanned aerial systems (UAS) is paramount to protecting small Soldier teams operating in remote battlefield scenarios. Currently, many small Unmanned Aerial Systems (sUAS) reconnaissance assets have the range necessary to facilitate small-unit missions. The purpose of this paper is to detail the design and testing of a system that fills this capability gap by creating folding-wing drones designed to be aerially deployed from an airdropped dispenser. The dispenser is attached to the Joint Precision Airdrop System (JPADS), which is an autonomously navigated cargo delivery parafoil that can glide several miles, and which can land within 100 meters of its target. To employ the system, the dispenser is launched from a high-altitude aircraft. The system must survive the opening of the parachute in high speed forward flight and provide cushioning to the drones and other components. Once the JPADS navigates the dispenser to a predetermined altitude and distance from the intended reconnaissance area, the dispenser deploys multiple folding-wing drones. The soldiers on the ground can access the drones’ live video feeds through a handheld video transmitter. The system combines the precision navigation and information-transmission capabilities of the fixed wing drone with the long-range capabilities of the JPADS. With a commercial-off-the-shelf drone as the folding-wing aircraft platform, the team designed a wing connection hub that allows for rapid folding and unfolding of the drone’s wings, a separate canister for each drone within the dispenser, and a dispenser capable of interfacing with both the canisters and the JPADS. Though currently in the technology-demonstration phase of the project, the team envisions the system being fully autonomous from launch of dispenser to end of mission.
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Vidalie, Julien, Imane Bouhali, Faida Mhenni, Michel Batteux, and Jean-Yves Choley. "Consistency of multiple system engineering models of a fixed wing drone." In 2022 IEEE International Symposium on Systems Engineering (ISSE). IEEE, 2022. http://dx.doi.org/10.1109/isse54508.2022.10005317.
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Carlos, Espinoza, Villasante Jorge, and Leonardo Vinces. "Design of a fixed-wing drone for blood packet delivery applications." In 21st LACCEI International Multi-Conference for Engineering, Education and Technology (LACCEI 2023): “Leadership in Education and Innovation in Engineering in the Framework of Global Transformations: Integration and Alliances for Integral Development”. Latin American and Caribbean Consortium of Engineering Institutions, 2023. http://dx.doi.org/10.18687/laccei2023.1.1.806.
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Saemi, Farid, Constandinos Mitsingas, Owen Dunston, and Moble Benedict. "In-flight Measurements and Validation of Electric Powertrain Models." In Vertical Flight Society 79th Annual Forum & Technology Display. The Vertical Flight Society, 2023. http://dx.doi.org/10.4050/f-0079-2023-18065.
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Small electric drones are popular vehicles for consumers and researchers. However, literature contains little data on in-flight aerodynamic loads that could validate aerodynamic or electric powertrain design tools. We developed a specially instrumented quadcopter to directly measure and record rotor torque and rotational speed during flight. We used this data to validate powertrain efficiency models for the motor, motor controller, and battery. The validated models predicted the time histories for battery discharge, controller current, and combined motor+controller efficiency within 5%, 20%, and 25% of experimental flight data respectively. The validated models can help engineers explore drone concepts without costly experiments and reduce program development costs. The novel flight data can help researchers validate other models, such as vehicle aerodynamic performance models. The modular instrumentation can help engineers measure analog signals onboard a flying vehicle for other applications, such as the wing loading on a fixed-wing drone.
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Caruccio, Danielle, Meaghan Rush, Peter Smith, James Carroll, Peter Warwick, Eric Smith, Caleb Fischer, et al. "Design, Fabrication, and Testing of the Fixed-Wing Air and Underwater Drone." In 17th AIAA Aviation Technology, Integration, and Operations Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4447.
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Alatorre, A., P. Castillo, and R. Lozano. "Least Airspeed Reduction Strategy & Flight Recuperation of a Fixed-Wing Drone." In 2021 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2021. http://dx.doi.org/10.1109/icuas51884.2021.9476680.
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Dong, Jingyi, and Datong Liu. "Sensor Data Prediction for Fixed-wing Drone Based on Online Sequential Learning." In 2022 IEEE International Instrumentation and Measurement Technology Conference (I2MTC). IEEE, 2022. http://dx.doi.org/10.1109/i2mtc48687.2022.9806574.
Full textReports on the topic "Fixed-wing drone"
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Grand-Clément, Sarah, and Theò Bajon. Uncrewed Aerial Systems: A Primer. UNIDIR, October 2022. http://dx.doi.org/10.37559/caap/22/erc/12.
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The production and use of uncrewed aerial systems (UASs) – which include vehicles that can be piloted either remotely or semi-autonomously – has increased. This primer introduces the different types of UAS (otherwise known as drones), including fixed-wing systems and rotary-wing systems such as quadcopters. It describes their key components and functions, as well as outlining the main challenges that these systems can pose to international security. The focus of the primer is on describing the main areas of technological innovation and development related to the key components that comprise UASs, outlining the anticipated areas of progress and potential concern.
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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), November 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.