Gotowe bibliografie tematyczne / Rotary-wing UAV

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Gotowa bibliografia na temat „Rotary-wing UAV”

Autor: Grafiati

Data publikacji: 4 czerwca 2021

Data aktualizacji: 19 lutego 2022

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Artykuły w czasopismach na temat "Rotary-wing UAV"

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

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

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Peng, Kemao. "Autonomous Mission Management Based Nonlinear Flight Control Design for a Class of Hybrid Unmanned Aerial Vehicles". Guidance, Navigation and Control 01, nr 02 (czerwiec 2021): 2150009. http://dx.doi.org/10.1142/s2737480721500096.

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In this paper, a nonlinear flight control law is designed for a hybrid unmanned aerial vehicle (UAV) to achieve the advanced flight performances with the autonomous mission management (AMM). The hybrid UAV is capable of hovering like quadrotors and maneuvering as fixed-wing aircraft. The main idea is to design the flight control laws in modules. Those modules are organized online by the autonomous mission management. Such online organization will improve the UAV autonomy. One of the challenges is to execute the transition flight between the rotary-wing and fixed-wing modes. The resulting closed-loop system with the designed flight control law is verified in simulation and the simulation results demonstrate that the resulting closed-loop system can successfully complete the designated flight missions including the transition flight between the rotary-wing and fixed-wing modes.

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ÜNAL, Beytullah, Tamer SAVAŞ i Işıl YAZAR. "DESIGN OF A SPRAYING QUADCOPTER". First Issue of 2019, nr 2019.01 (18.12.2019): 3–9. http://dx.doi.org/10.23890/ijast.2019.0101.

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Today, coupled with technological development, UAV (Unmanned Aero Vehicle) systems show an important improvement in civil area applications. UAV systems have active tasks with cost-effectively solutions in several areas like defense, logistics, engineering and agriculture. Especially, in agricultural applications, UAV system usage contributes to development of the critical parameters of this sector as efficiency and sustainability. Thus, in agricultural areas, improvement and usage of unmanned systems are of importance. In this study, a remote control rotary wing UAV system that has ability to perform irrigation and spraying and its design, production and application processes are discussed. The designed, verified and all test operations completed UAV system will be planned to use in remote control liquid rejection from different altitudes in agricultural area. Keywords: Unmanned Aircraft Vehicle (UAV), Rotary Wing UAV, Spraying, Remote Control UAV, Sustainability.

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Gonzalez, José Cerdeira, Roberto Ortiz Garrido i Antonio Eduardo Carrilho da Cunha. "Rotary-Wing UAV Mission Planning Aided by Supervisory Control". IFAC Proceedings Volumes 43, nr 12 (2010): 324–30. http://dx.doi.org/10.3182/20100830-3-de-4013.00054.

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Zhan, Cheng, i Renjie Huang. "Energy Efficient Adaptive Video Streaming With Rotary-Wing UAV". IEEE Transactions on Vehicular Technology 69, nr 7 (lipiec 2020): 8040–44. http://dx.doi.org/10.1109/tvt.2020.2993303.

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Ahmed, Bilal, Hemanshu R. Pota i Matt Garratt. "Flight control of a rotary wing UAV using backstepping". International Journal of Robust and Nonlinear Control 20, nr 6 (12.05.2009): 639–58. http://dx.doi.org/10.1002/rnc.1458.

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Zeng, Yong, Jie Xu i Rui Zhang. "Energy Minimization for Wireless Communication With Rotary-Wing UAV". IEEE Transactions on Wireless Communications 18, nr 4 (kwiecień 2019): 2329–45. http://dx.doi.org/10.1109/twc.2019.2902559.

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Yan, Hua, Yunfei Chen i Shuang-Hua Yang. "New Energy Consumption Model for Rotary-Wing UAV Propulsion". IEEE Wireless Communications Letters 10, nr 9 (wrzesień 2021): 2009–12. http://dx.doi.org/10.1109/lwc.2021.3090772.

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Guo, Huiqiang, Mingzhe Li, Pengfei Sun, Changfeng Zhao, Wenjie Zuo i Xiaoying Li. "Lightweight and maintainable rotary-wing UAV frame from configurable design to detailed design". Advances in Mechanical Engineering 13, nr 7 (lipiec 2021): 168781402110349. http://dx.doi.org/10.1177/16878140211034999.

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Rotary-wing unmanned aerial vehicles (UAVs) are widespread in both the military and civilian applications. However, there are still some problems for the UAV design such as the long design period, high manufacturing cost, and difficulty in maintenance. Therefore, this paper proposes a novel design method to obtain a lightweight and maintainable UAV frame from configurable design to detailed design. First, configurable design is implemented to determine the initial design domain of the UAV frame. Second, topology optimization method based on inertia relief theory is used to transform the initial geometric model into the UAV frame structure. Third, process design is considered to improve the manufacturability and maintainability of the UAV frame. Finally, dynamic drop test is used to validate the crashworthiness of the UAV frame. Therefore, a lightweight UAV frame structure composed of thin-walled parts can be obtained and the design period can be greatly reduced via the proposed method.

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Kumar, K. Senthil, i A. Mohamed Rasheed. "Development of Rotary Wing Mini UAS for Civilian Applications". Unmanned Systems 01, nr 02 (październik 2013): 247–58. http://dx.doi.org/10.1142/s2301385013400050.

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This research paper is about team Dhaksha's accomplishment in designing, developing and testing a slew of Rotary Wing Mini Unmanned Aerial Systems for entry into various international aerial robotics/unmanned aerial vehicle (UAV) competitions and civilian applications. Dhaksha, the Unmanned Aircraft System (UAS), developed by the team at Madras Institute of Technology (MIT) campus of Anna University, Chennai, Tamil Nadu, India, with its stable design presented stiff competition to other contestants during the May 2012 technology demonstration called UAVForge organized by Defense Advanced Research Project Agency (DARPA), Department of Defense, USA. Team Dhaksha on behalf of national defense research agency deployed their system as a test bed for Acoustic field testing and analysis. The team also deployed their UAS, for state police, in a religious festival, over a crowd of 20 lakh pilgrims during November 2012, to avail instant aerial images. UAS Dhaksha was deployed for investigation of structural strength of the India's tallest structure, a 300 m high Reinforced Cement Concrete (RCC) tower. Recently during the flash floods in the Himalayan river Mandakini at an altitude of 4200 m above mean sea level, Dhaksha assisted the forces in the relief and rescue operations by providing instant thermal/video images of the scene of disaster.

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Rozprawy doktorskie na temat "Rotary-wing UAV"

Beyers, Coenraad Johannes. "Motion planning algorithms for autonomous navigation for a rotary-wing UAV". Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/80231.

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Thesis (MScEng)--Stellenbosch University, 2013.
ENGLISH ABSTRACT: This project concerns motion planning for a rotary wing UAV, where vehicle controllers are already in place, and map data is readily available to a collision detection module. In broad terms, the goal of the motion planning algorithm is to provide a safe (i.e. obstacle free) flight path between an initial- and goal waypoint. This project looks at two specific motion planning algorithms, the Rapidly Exploring Random Tree (or RRT*), and the Probabilistic Roadmap Method (or PRM). The primary focus of this project is learning how these algorithms behave in specific environments and an in depth analysis is done on their differences. A secondary focus is the execution of planned paths via a Simulink simulation and lastly, this project also looks at the effect of path replanning. The work done in this project enables a rotary wing UAV to autonomously navigate an uncertain, dynamic and cluttered environment. The work also provides insight into the choice of an algorithm for a given environment: knowing which algorithm performs better can save valuable processing time and will make the entire system more responsive.
AFRIKAANSE OPSOMMING: ’n Tipiese vliegstuuroutomaat is daartoe in staat om ’n onbemande lugvaartvoertuig (UAV) so te stuur dat ’n stel gedefinieerde punte gevolg word. Die punte moet egter vooraf beplan word, en indien enige verandering nodig is (bv. as gevolg van veranderinge in die omgewing) is dit nodig dat ’n menslike operateur betrokke moet raak. Vir voertuie om ten volle outonoom te kan navigeer, moet die voertuig in staat wees om te kan reageer op veranderende situasies. Vir hierdie doel word kinodinamiese beplanningsalgoritmes en konflikdeteksiemetodes gebruik. Hierdie projek behels kinodinamiese beplanningsalgoritmes vir ’n onbemande helikopter, waar die beheerders vir die voertuig reeds in plek is, en omgewingsdata beskikbaar is vir ’n konflikdeteksie-module. In breë terme is die doel van die kinodinamiese beplanningsalgoritme om ’n veilige (d.w.s ’n konflikvrye) vlugpad tussen ’n begin- en eindpunt te vind. Hierdie projek kyk na twee spesifieke kinodinamiese beplanningsalgoritmes, die “Rapidly exploring Random Tree*” (of RRT*), en die “Probabilistic Roadmap Method” (of PRM). Die primêre fokus van hierdie projek is om die gedrag van hierdie algoritmes in spesifieke omgewings te analiseer en ’n volledige analise te doen op hul verskille. ’n Sekondêre fokus is die uitvoering van ’n beplande vlugpad d.m.v ’n Simulink-simulasie, en laastens kyk hierdie projek ook na die effek van padherbeplanning. Die werk wat gedoen is in hierdie projek stel ’n onbemande helikopter in staat om outonoom te navigeer in ’n onsekere, dinamiese en besige omgewing. Die werk bied ook insig in die keuse van ’n algoritme vir ’n gegewe omgewing: om te weet watter algoritme beter uitvoertye het kan waardevolle verwerkingstyd bespaar, en verseker dat die hele stelsel vinniger kan reageer.

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Kang, Keeryun. "Online optimal obstacle avoidance for rotary-wing autonomous unmanned aerial vehicles". Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/44820.

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This thesis presents an integrated framework for online obstacle avoidance of rotary-wing unmanned aerial vehicles (UAVs), which can provide UAVs an obstacle field navigation capability in a partially or completely unknown obstacle-rich environment. The framework is composed of a LIDAR interface, a local obstacle grid generation, a receding horizon (RH) trajectory optimizer, a global shortest path search algorithm, and a climb rate limit detection logic. The key feature of the framework is the use of an optimization-based trajectory generation in which the obstacle avoidance problem is formulated as a nonlinear trajectory optimization problem with state and input constraints over the finite range of the sensor. This local trajectory optimization is combined with a global path search algorithm which provides a useful initial guess to the nonlinear optimization solver. Optimization is the natural process of finding the best trajectory that is dynamically feasible, safe within the vehicle's flight envelope, and collision-free at the same time. The optimal trajectory is continuously updated in real time by the numerical optimization solver, Nonlinear Trajectory Generation (NTG), which is a direct solver based on the spline approximation of trajectory for dynamically flat systems. In fact, the overall approach of this thesis to finding the optimal trajectory is similar to the model predictive control (MPC) or the receding horizon control (RHC), except that this thesis followed a two-layer design; thus, the optimal solution works as a guidance command to be followed by the controller of the vehicle. The framework is implemented in a real-time simulation environment, the Georgia Tech UAV Simulation Tool (GUST), and integrated in the onboard software of the rotary-wing UAV test-bed at Georgia Tech. Initially, the 2D vertical avoidance capability of real obstacles was tested in flight. Then the flight test evaluations were extended to the benchmark tests for 3D avoidance capability over the virtual obstacles, and finally it was demonstrated on real obstacles located at the McKenna MOUT site in Fort Benning, Georgia. Simulations and flight test evaluations demonstrate the feasibility of the developed framework for UAV applications involving low-altitude flight in an urban area.

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McEwen, Matthew D. "Dynamic system identification and modeling of a rotary wing UAV for stability and control analysis". Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1998. http://handle.dtic.mil/100.2/ADA349878.

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Gleeson, Jeremy Information Technology &amp Electrical Engineering Australian Defence Force Academy UNSW. "Finding the shipboard relative position of a rotary wing unmanned aerial vehicle (UAV) with ultasonic ranging". Awarded by:University of New South Wales - Australian Defence Force Academy, 2008. http://handle.unsw.edu.au/1959.4/38978.

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Simple, cheap and reliable echo-based ultrasonic ranging systems such as the Polaroid ranging unit are easily applied to indoor applications. However, to measure the range between an unmanned helicopter and a moving ship deck at sea using ultrasound requires a more robust ranging system, because rushing air and breaking water are known ultrasound noise sources. The work of designing, constructing and testing such a system is described in this dissertation. The compact, UAV ready ultrasound transmitter module provides high power, broadband arbitrary signal generation. The separate field-ready receiver is based on a modern embedded Digital Signal Processor (DSP), providing high speed matched-filter correlation processing. Large time-bandwidth signalling is employed to maximise the signal to noise ratio of the ranging system. Synthesised experiments demonstrate the ability of the correlation processing to reliably recover timing from signals buried in noise. Real world experiments demonstrate decimetre accuracy with two centimetre resolution, ten metre range and 32Hz refresh rate. A maximum boresight range of up to 38m is supported.

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Rathore, Ankush, i ankushrathore@yahoo com. "A systems approach to model the conceptual design process of vertical take-off unmanned aerial vehicle". RMIT University. School of Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20061114.103443.

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The development and induction in-service of Unmanned Air Vehicles (UAV) systems in a variety of civil, paramilitary and military roles have proven valuable on high-risk missions. These UAVs based on fixed wing configuration concept have demonstrated their operational effectiveness in recent operations. New UAVs based on rotary wing configuration concept have received major attention worldwide, with major resources committed for its research and development. In this thesis, the design process of a rotary-wing aircraft was re-visualised from an unmanned perspective to address the requirements of rotary-wing UAVs - Vertical Take-off UAVs (VTUAV). It investigates the conventional helicopter design methodology for application in UAV design. It further develops a modified design process for VTUAV addressing the requirements of unmanned missions by providing remote command-and-control capabilities. The modified design methodology is automated to address the complex design evaluations and optimisation process. An illustration of the automated design process developed for VTUAVs is provided through a series of inputs of the requirements and specifications, resulting in an output of a proposed VTUAV design configuration for

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Ma, Ling. "Development of Fault Detection and Diagnosis Techniques with Applications to Fixed-wing and Rotary-wing UAVs". Thesis, 2011. http://spectrum.library.concordia.ca/7466/1/MA_MASc_S20..pdf.

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ABSTRACT Development of Fault Detection and Diagnosis Techniques with Applications to Fixed-wing and Rotary-wing UAVs Ling Ma Fault Detection and Diagnosis (FDD), as the central part of a Fault Tolerant Control System (FTCS), detects and diagnoses the source and the magnitude of a fault when a fault/failure occurs either in an actuator, sensor or in the system itself. This thesis work develops an applicable procedure for a FDD scheme to both fixed-wing and rotary-wing UAVs (Unmanned Aerial Vehicles) in the discrete-time stochastic domain based on the Kalman filter techniques. In particular, the proposed techniques are developed in highly nonlinear and 6 degree-of-freedom equations of Matlab/Simulink simulation environment for a quad-rotor helicopter UAV, a Boeing 747, and a NASA Generic Transport Model (GTM) fixed-wing UAV. A key development in this thesis is that an Adaptive Two-Stage Extended Kalman Filter (ATSEKF) algorithm and a Dual Unscented Kalman Filter (DUKF) algorithm are applied for simultaneous states and fault parameters estimation of these UAVs. The statistical decision-making techniques for fault detection and diagnosis are also discussed in the presence of partial faults in the UAVs. The measured system outputs and control signals are used as inputs of the ATSEKF and DUKF, and the estimated states and parameters are used for comparison and analysis in the fault detection and diagnosis. The simulation results show that the effectiveness and performance of ATSEKF and DUKF for the purpose of fault detection and diagnosis of both fixed- and rotary-wing UAVs are satisfactory.

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Książki na temat "Rotary-wing UAV"

McEwen, Matthew D. Dynamic system identification and modeling of a rotary wing UAV for stability and control analysis. Monterey, Calif: Naval Postgraduate School, 1998.

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Dynamic System Identification and Modeling of a Rotary Wing UAV for Stability and Control Analysis. Storming Media, 1998.

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Części książek na temat "Rotary-wing UAV"

Wu, Fahui, Dingcheng Yang i Lin Xiao. "Energy Minimization for Rotary-Wing UAV Enabled WPCN". W Intelligent Robotics and Applications, 27–40. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-27538-9_3.

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Ahmed, Bilal, i Hemanshu R. Pota. "Dynamic Compensation for Control of a Rotary wing UAV Using Positive Position Feedback". W Unmanned Aerial Vehicles, 43–56. Dordrecht: Springer Netherlands, 2010. http://dx.doi.org/10.1007/978-94-007-1110-5_5.

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Göktoğan, Ali Haydar, Salah Sukkarieh, Mitch Bryson, Jeremy Randle, Todd Lupton i Calvin Hung. "A Rotary-wing Unmanned Air Vehicle for Aquatic Weed Surveillance and Management". W Selected papers from the 2nd International Symposium on UAVs, Reno, Nevada, U.S.A. June 8–10, 2009, 467–84. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-90-481-8764-5_24.

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Gomes, Alexandre, Bruno J. Guerreiro, Rita Cunha, Carlos Silvestre i Paulo Oliveira. "Sensor-Based 3-D Pose Estimation and Control of Rotary-Wing UAVs Using a 2-D LiDAR". W ROBOT 2017: Third Iberian Robotics Conference, 718–29. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-70833-1_58.

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Streszczenia konferencji na temat "Rotary-wing UAV"

Xu, Yaojin, Long Di i YangQuan Chen. "Consensus Based Formation Control of Multiple Small Rotary-Wing UAVs". W ASME 2011 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/detc2011-47844.

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Small unmanned aerial vehicles (UAVs) can provide facilities in various applications. Compared with single UAV system, small UAVs based cooperative UAV system can bring advantages such as higher efficiency and safety. Therefore, it is necessary to design a robust multi-agent cooperative flight controller to coordinate a group of small UAVs for stable formation flights. This paper investigates the problem of consensus-based formation control for a multi-UAV system. Firstly, We choose a simplified model with nonholonomic constraints for UAV dynamics. Secondly, using the algebraic theory and backstepping technique, we design consensus protocols for multi-UAV systems under the strongly connected topology. Then based on that, we propose a multi-UAVfromation control strategy. Finally, we extend our results to the directed topology case which is still effective by simulation.

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Bilal Ahmed, Hemanshu R. Pota i Matt Garratt. "Rotary wing UAV position control using backstepping". W 2007 46th IEEE Conference on Decision and Control. IEEE, 2007. http://dx.doi.org/10.1109/cdc.2007.4434589.

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Hui Xie, Alan Lynch i Martin Jagersand. "IBVS of a rotary wing UAV using line features". W 2014 IEEE 27th Canadian Conference on Electrical and Computer Engineering (CCECE). IEEE, 2014. http://dx.doi.org/10.1109/ccece.2014.6901119.

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Hanford, Scott, Lyle Long i Joseph Horn. "A Small Semi-Autonomous Rotary-Wing Unmanned Air Vehicle (UAV)". W Infotech@Aerospace. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-7077.

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Ahmed, Bilal, Hemanshu R. Pota i Matt Garratt. "Flight control of a rotary wing UAV - a practical approach". W 2008 47th IEEE Conference on Decision and Control. IEEE, 2008. http://dx.doi.org/10.1109/cdc.2008.4738917.

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Grobler, P. R., i H. W. Jordaan. "Autonomous Vision Based Landing Strategy for a Rotary Wing UAV". W 2020 International SAUPEC/RobMech/PRASA Conference. IEEE, 2020. http://dx.doi.org/10.1109/saupec/robmech/prasa48453.2020.9041238.

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Ahmed, Bilal, i Hemanshu R. Pota. "Flight control of a Rotary wing UAV using adaptive backstepping". W 2009 IEEE International Conference on Control and Automation (ICCA). IEEE, 2009. http://dx.doi.org/10.1109/icca.2009.5410398.

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Kong, Changduk, Jongha Park i Myoungcheol Kang. "A Study on Transient Performance Characteristics of the CRW Type UAV Propulsion System During Flight Mode Transition". W ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68400.

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A propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) was composed of the turbojet engine, exhaust nozzles including some tip jet nozzles and a main nozzle and the duct system including straight ducts, curved ducts and master valve. The CRW type UAV has three different flight modes such as the rotary wing mode for take-off and landing, the high-speed forward flight mode with the fixed wing and the transition flight mode between the previously mentioned two flight modes. In order to evaluate transient performance characteristics of the CRW type UAV propulsion system during flight mode transition, the propulsion system was modeled using SIMULINK®, which is an user-friendly GUI type dynamic analysis tool provided by MATLAB, in this study. Considering area variation of the master valve and the main exhaust nozzle simulated the transition flight mode between the rotary wing mode and the fixed wing mode. In order to verify acceptability of the main turbojet engine model, performance simulation results using SIMULINK® were compared with results using the commercial program GSP. Moreover the performance characteristics of the propulsion system were investigated depending on position angle variation of the master valve at both the rotary wing mode and the fixed wing mode. In the transient performance behaviors at the rotary wing flight mode, the more turbine inlet temperature over shoot occurs and the net thrust at tip jet nozzles, decreases rapidly at initial condition then increase fast to the converged steady-state condition. Therefore, the fuel throttle should be slowly performed for safe operation of engine. During flight mode transition from the rotary wing mode to the fixed wing mode, rotary duct pressure was fell down to atmospheric pressure, but main duct pressure was mostly kept due to very small friction loss. Total net thrust was oscillatory increased. During flight mode transition from the fixed wing mode to rotary wing mode, rotary duct pressure was rapidly increased, but main duct pressure was mostly kept. Total net thrust also was oscillatory decreased. Through this investigation, it was found that severe thrust fluctuation should be considered for safe flight during flight mode transition even though operation of the master valve is slowly scheduled. Therefore a solution for improving the thrust oscillation will be suggested later.

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Wheeler, Jei. "Tactical Close Aerial Support for Public Events by Rotary Wing UAV". W Infotech@Aerospace. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-6953.

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Sanchez, L. A., O. Santos, H. Romero, S. Salazar i R. Lozano. "Nonlinear and optimal real-time control of a rotary-wing UAV". W 2012 American Control Conference - ACC 2012. IEEE, 2012. http://dx.doi.org/10.1109/acc.2012.6315498.

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