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Dissertations / Theses on the topic 'Unmanned helicopters'

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Published: 4 June 2021
Last updated: 16 February 2022

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1

Dalamagkidis, Konstantinos. "Autonomous vertical autorotation for unmanned helicopters." [Tampa, Fla] : University of South Florida, 2009. http://purl.fcla.edu/usf/dc/et/SFE0003147.

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2

Eck, Christoph. "Navigation algorithms with applications to unmanned helicopters /." Zürich : IMRT Press c/o Institut für Mess- und Regeltechnik, ETH Zentrum, 2001. http://e-collection.ethbib.ethz.ch/show?type=diss&nr=14402.

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3

Gatzke, Benjamin Thomas. "Trajectory optimization for helicopter Unmanned Aerial Vehicles (UAVs)." Thesis, Monterey, California : Naval Postgraduate School, 2010. http://edocs.nps.edu/npspubs/scholarly/theses/2010/Jun/10Jun%5FGatzke.pdf.

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Thesis (M.S. in Applied Mathematics)--Naval Postgraduate School, June 2010.<br>Thesis Advisor(s): Kang, Wei ; Second Reader: Zhou, Hong. "June 2010." Description based on title screen as viewed on July 14, 2010. Author(s) subject terms: Nonlinear model, trajectory optimization, state and control variables, cost function Includes bibliographical references (p. 59-60). Also available in print.
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4

Van, Schalkwyk Carlo. "Full state control of a Fury X-Cell unmanned helicopter." Thesis, Stellenbosch : University of Stellenbosch, 2009. http://hdl.handle.net/10019.1/2934.

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Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2009.<br>This thesis describes the successful development of an autopilot for an unmanned radio controlled helicopter. It presents a non-linear helicopter model. An adaptive linearised model is derived and used to design a controller. The adaptive full state controller is tested in various ways, including two aerobatic manoeuvres. A number of analyses are performed on the controller, including its robustness to parameter changes, noisy estimates, wind and processing power. The controller is compared with
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5

Zhang, Lin. "Control strategies and stability analysis of small-scale unmanned helicopters." Thesis, University of Manchester, 2017. https://www.research.manchester.ac.uk/portal/en/theses/control-strategies-and-stability-analysisof-smallscale-unmanned-helicopters(8e4f8464-6fdd-42e2-9362-033a57a128b2).html.

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This thesis presents the design and the stability analysis of a hierarchical controller for unmanned aerial vehicles. We utilize non-linear control methodology to command dynamics of unmanned helicopter which has been divided into slower translational dynamics (outer-loop) and faster orientation dynamics (inner-loop), thus exhibiting hierarchical structure. The attitude angles and position which separately belongs to the inner-loop and the outer-loop can be independently controlled by backstepping control strategy. Stability analysis of the helicopter system including applying dynamics has bee
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6

Bin, Xu, Zhang XiaoLin, Lu Guolei, and Hu Weiwei. "THE BASE STATION TELEMETRY DATA PROCESSING SYSTEM FOR UNMANNED HELICOPTERS." International Foundation for Telemetering, 2004. http://hdl.handle.net/10150/605311.

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International Telemetering Conference Proceedings / October 18-21, 2004 / Town & Country Resort, San Diego, California<br>This paper discusses the design and implementation of the base station telemetry data processing system for the unmanned helicopter. The system designed is composed of code synchronizer, decoding and frame synchronizer as well as PCI bus interface. The functions of the system are implemented with very large integrated circuits and a standard PCI inserted card that is compact and easy to install. The result of flight performance tests shows that the system is reliable an
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7

Irwin, Shaun George. "Optimal estimation and sensor selection for autonomous landing of a helicopter on a ship deck." Thesis, Stellenbosch : Stellenbosch University, 2014. http://hdl.handle.net/10019.1/95894.

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Thesis (MEng)--Stellenbosch University, 2014.<br>ENGLISH ABSTRACT: This thesis presents a complete state estimation framework for landing an unmanned helicopter on a ship deck. In order to design and simulate an optimal state estimator, realistic sensor models are required. Selected inertial, absolute and relative sensors are modeled based on extensive data analysis. The short-listed relative sensors include monocular vision, stereo vision and laser-based sensors. A state estimation framework is developed to fuse available helicopter estimates, ship estimates and relative measurements. T
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8

Poyi, Gwangtim Timothy. "A novel approach to the control of quad-rotor helicopters using fuzzy-neural networks." Thesis, University of Derby, 2014. http://hdl.handle.net/10545/337911.

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Quad-rotor helicopters are agile aircraft which are lifted and propelled by four rotors. Unlike traditional helicopters, they do not require a tail-rotor to control yaw, but can use four smaller fixed-pitch rotors. However, without an intelligent control system it is very difficult for a human to successfully fly and manoeuvre such a vehicle. Thus, most of recent research has focused on small unmanned aerial vehicles, such that advanced embedded control systems could be developed to control these aircrafts. Vehicles of this nature are very useful when it comes to situations that require unmann
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9

Swart, Andre Dewald. "Monocular vision assisted autonomous landing of a helicopter on a moving deck." Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/80134.

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Thesis (MScEng)--Stellenbosch University, 2013.<br>ENGLISH ABSTRACT: The landing phase of any helicopter is the most critical part of the whole flight envelope, particularly on a moving flight deck. The flight deck is usually located at the stern of the ship, translating to large heave motions. This thesis focuses on the three fundamental components required for a successful landing: accurate, relative state-estimation between the helicopter and the flight deck; a prediction horizon to forecast suitable landing opportunities; and excellent control to safely unite the helicopter with the f
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10

Kadmiry, Bourhane. "Fuzzy Control for an Unmanned Helicopter." Licentiate thesis, Linköping University, Linköping University, AUTTEK - Autonomous Unmanned Aerial Vehicle Research Group, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-5723.

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<p>The overall objective of the Wallenberg Laboratory for Information Technology and Autonomous Systems (WITAS) at Linköping University is the development of an intelligent command and control system, containing vision sensors, which supports the operation of a unmanned air vehicle (UAV) in both semi- and full-autonomy modes. One of the UAV platforms of choice is the APID-MK3 unmanned helicopter, by Scandicraft Systems AB. The intended operational environment is over widely varying geographical terrain with traffic networks and vehicle interaction of variable complexity, speed, and density.</p
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11

Riddell, Kevin Donald Alexander. "Design, testing and demonstration of a small unmanned aircraft system (SUAS) and payload for measuring wind speed and particulate matter in the atmospheric boundary layer." Thesis, Arts and Science, 2014. http://hdl.handle.net/10133/3416.

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The atmospheric boundary layer (ABL) is the layer of air directly influenced by the Earth’s surface and is the layer of the atmosphere most important to humans as this is the air we live in. Methods for measuring the properties of the ABL include three general approaches: satellite-based, ground- based and airborne. A major research challenge is that many contemporary methods provide a restricted spatial resolution or coverage of variations of ABL properties such as how wind speed varies across a landscape with complex topography. To enhance our capacity to measure the properties of the ABL, t
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12

Karasu, Caglar. "Small-size Unmanned Model Helicopter Guidance And Control." Master's thesis, METU, 2004. http://etd.lib.metu.edu.tr/upload/12605595/index.pdf.

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The deployment of unmanned aerial vehicles (UAV) in military applications increased the research about them and the importance of them. The unmanned helicopters are the most agile and maneuverable vehicles among the unmanned aerial vehicles (UAV). The ability of hovering and low speed cruise makes them even more attractive. Such abilities supply more areas to deploy the usage of the unmanned helicopters like search &amp<br>rescue, mapping, surveillance. Autonomy is the key property for these vehicles. In order to provide autonomy to an unmanned vehicle, the guidance and the autopilot units are
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13

May, James. "Tethered Payload Control from an Autonomous Helicopter." Thesis, Virginia Tech, 2010. http://hdl.handle.net/10919/35331.

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A system is designed to deploy and support a tethered ground robot from an autonomous helicopter. A winch is designed and built. Electrical hardware for power distribution and control are designed. Several applied controls problems are investigated. A control architecture is established and low level controllers are designed to meet the demands of two higher level algorithms. A tether tension controller is designed to avoid the danger of excess slack in the tether interfering with the robot's mobility. A payload sway damping controller is investigated and simulated. Its is shown to be eective
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14

Davis, Joshua Daniel. "Motion planning under uncertainty: application to an unmanned helicopter." Texas A&M University, 2006. http://hdl.handle.net/1969.1/4280.

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A methodology is presented in this work for intelligent motion planning in an uncertain environment using a non-local sensor, like a radar sensor, that allows the sensing of the environment non-locally. This methodology is applied to an unmanned helicopter navigating a cluttered urban environment. It is shown that the problem of motion planning in a uncertain environment, under certain assumptions, can be posed as the adaptive optimal control of an uncertain Markov Decision Process, characterized by a known, control dependent system, and an unknown, control independent environment. The strateg
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15

Kadmiry, Bourhane. "Fuzzy gain scheduled visual servoing for an unmanned helicopter /." Linköping : Dept. of Computer and Information Science, Univ, 2005. http://www.bibl.liu.se/liupubl/disp/disp2005/tek938s.pdf.

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16

McCabe, Brian John. "Underslung Payload Tension Control from an Autonomous Unmanned Helicopter." Thesis, Virginia Tech, 2012. http://hdl.handle.net/10919/32679.

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A tension control algorithm for the deployment of a unmanned ground vehicle from an autonomous helicopter is designed and tested in this thesis. The physical hardware which the controller will run on is detailed. The plant model and underlying controllers are derived and modeled. The tension controller algorithm is selected, derived, and modeled. The parameters of the tension controller are chosen and simulations are run with the chosen parameters. The tension control algorithm is run on the physical hardware, successfully demonstrating tension control on a ground vehicle. Robustness simulatio
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17

Samal, Mahendra Engineering &amp Information Technology Australian Defence Force Academy UNSW. "Neural network based identification and control of an unmanned helicopter." Awarded by:University of New South Wales - Australian Defence Force Academy. Engineering & Information Technology, 2009. http://handle.unsw.edu.au/1959.4/43917.

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This research work provides the development of an Adaptive Flight Control System (AFCS) for autonomous hover of a Rotary-wing Unmanned Aerial Vehicle (RUAV). Due to the complex, nonlinear and time-varying dynamics of the RUAV, indirect adaptive control using the Model Predictive Control (MPC) is utilised. The performance of the MPC mainly depends on the model of the RUAV used for predicting the future behaviour. Due to the complexities associated with the RUAV dynamics, a neural network based black box identification technique is used for modelling the behaviour of the RUAV. Auto-regres
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18

Drozeski, Graham R. "A Fault-Tolerant Control Architecture for Unmanned Aerial Vehicles." Diss., Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/7523.

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Research has presented several approaches to achieve varying degrees of fault-tolerance in unmanned aircraft. Approaches in reconfigurable flight control are generally divided into two categories: those which incorporate multiple non-adaptive controllers and switch between them based on the output of a fault detection and identification element and those that employ a single adaptive controller capable of compensating for a variety of fault modes. Regardless of the approach for reconfigurable flight control, certain fault modes dictate system restructuring in order to prevent a catastrophic fa
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19

Östman, Christian, and Anna Forsberg. "Support System for Landing with an Autonomous Unmanned Aerial Vehicle." Thesis, Linköping University, Linköping University, Linköping University, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-16278.

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<p>There are a number of ongoing projects developing autonomous vehicles, both helicopters and airplanes. The purpose of this thesis is to study a concept for calculating the height and attitude of a helicopter. The system will be active during landing. This thesis includes building an experimental setup and to develop algorithms and software.</p><p>The basic idea is to illuminate the ground with a certain pattern and in our case we used laser pointers to create this pattern. The ground is then filmed and the images are processed to extract the pattern. This provides us with information about
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20

Adams, Jerrod C. "An Interpolation Approach to Optimal Trajectory Planning for Helicopter Unmanned Aerial Vehicles." Thesis, Monterey, California. Naval Postgraduate School, 2012. http://hdl.handle.net/10945/7300.

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This thesis explores numerical methods to provide real-time control inputs to achieve an optimal trajectory which minimizes the time required for a Helicopter Unmanned Aerial Vehicle (HUAV) to reorient to a given target. A library of optimal trajectories is populated using a pseudospectral computational algorithm applied to the mathematical model developed by the National University of Singapore and Singapore Department of Defense to simulate flight characteristics for their HeLion small scale HUAV system. The model is a complex system of non-linear differential equationsfifteen state variable
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21

Arlinghaus, Mark C. "Autopilot Development for an RC Helicopter." Wright State University / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=wright1259002743.

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22

Bellstedt, Philip. "The design, implementation of a moving platform landing algorithm for an unmanned autonomous helicopter." Thesis, Stellenbosch : Stellenbosch University, 2015. http://hdl.handle.net/10019.1/96780.

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Thesis (MSc)--Stellenbosch University, 2015.<br>ENGLISH ABSTRACT: With a view to future ship deck landings, a moving platform landing algorithm for an unmanned autonomous helicopter was successfully designed and a number of systems were developed in order to implement the landing algorithm. Through a combination of an MCA-based ship motion prediction algorithm and the appropriate analysis of platform motion criteria, a system was developed which can identify valid landing opportunities in real ship motion data recorded at sea state 4 for up to 5 s into the future with a 75% success rate. The
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23

Aldawoodi, Namir. "An approach to designing an unmanned helicopter autopilot using genetic algorithms and simulated annealing." [Tampa, Fla] : University of South Florida, 2008. http://purl.fcla.edu/usf/dc/et/SFE0002458.

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24

Raptis, Ioannis A. "Linear and Nonlinear Control of Unmanned Rotorcraft." Scholar Commons, 2009. http://scholarcommons.usf.edu/etd/3482.

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The main characteristic attribute of the rotorcraft is the use of rotary wings to produce the thrust force necessary for motion. Therefore, rotorcraft have an advantage relative to fixed wing aircraft because they do not require any relative velocity to produce aerodynamic forces. Rotorcraft have been used in a wide range of missions of civilian and military applications. Particular interest has been concentrated in applications related to search and rescue in environments that impose restrictions to human presence and interference. The main representative of the rotorcraft family is the helic
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25

Zarovy, Samuel R. "Improved gust rejection for a micro coaxial helicopter in urban environments." Diss., Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/52992.

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Due to their small size, relative covertness, and high maneuverability, micro rotorcraft are ideal for a plethora of civilian and military applications in an urban environment such as, surveillance, monitoring, mapping, and search and rescue. It is envisioned that these vehicles will operate indoors confined complex spaces, and outside near the ground—among buildings and other obstacles. The aerodynamic velocity fields in these areas are notoriously complex with the mean winds varying spatially and temporally with sharp changes in wind magnitude and direction over small distances. This results
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26

Martinos, Ioannis 1977. "Experiments in real time path planning for a small unmanned helicopter using mixed integer linear programming." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/17046.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2003.<br>Includes bibliographical references (leaves 56-57).<br>This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.<br>We use mathematical programming to perform simulated and actual flight experiments with the MIT autonomous helicopter platform. The experimental platform mechanical hardware, avionics and software architecture are described. Mixed Integer Linear Programming formulations for guidance experimen
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27

Haslum, Patrik. "Prediction as a Knowledge Representation Problem : A Case Study in Model Design." Licentiate thesis, Linköping University, Linköping University, KPLAB - Knowledge Processing Lab, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-5724.

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<p>The WITAS project aims to develop technologies to enable an Unmanned Airial Vehicle (UAV) to operate autonomously and intelligently, in applications such as traffic surveillance and remote photogrammetry. Many of the necessary control and reasoning tasks, e.g. state estimation, reidentification, planning and diagnosis, involve prediction as an important component. Prediction relies on models, and such models can take a variety of forms. Model design involves many choices with many alternatives for each choice, and each alternative carries advantages and disadvantages that may be far from ob
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28

Hermansson, Joel. "Vision and GPS based autonomous landing of an unmanned aerial vehicle." Thesis, Linköping University, Automatic Control, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-57735.

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<p>A control system for autonomous landing of an unmanned aerial vehicle (UAV)with high precision has been developed. The UAV is a medium sized model he-licopter. Measurements from a GPS, a camera and a compass are fused with anextended Kalman filter for state estimation of the helicopter. Four PID-controllers,one for each control signal of the helicopter, are used for the helicopter control.During the final test flights fifteen landings were performed with an average land-ing accuracy of 35 cm.    A bias in the GPS measurements makes it impossible to land the helicopter withhigh precision usi
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29

Kontitsis, Michail. "Design and implementation of an integrated dynamic vision system for autonomous systems operating in uncertain domains." [Tampa, Fla] : University of South Florida, 2009. http://purl.fcla.edu/usf/dc/et/SFE0002852.

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30

Berg, Tobias, and David Carlsson. "Mekanisk säkring av helikopter på fartygsdäck : en konceptuell fallstudie av Saabs UAV-system Skeldar M." Thesis, Linköping University, Department of Management and Engineering, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-11233.

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<p>Den senaste trenden inom flygvapenindustrin är utveckling av obemannade farkoster. Den svenska vapenindustrikoncernen Saab AB följer denna trend i och med den stundande introduktionen av företagets obemannade helikopter Skeldar V-150. Som ett led i vidareutvecklingen av detta system finns planer på att även lansera en marin variant, kallad Skeldar M. Tanken med denna marina variant är att möjliggöra fullständigt autonoma starter och landningar från fartyg. För att kunna genomföra detta på ett tryggt sätt även i hårt väder krävs att helikoptern hålls säkrad på fartygsdäcket såväl innan start
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31

Strenzke, Ruben [Verfasser], Axel [Akademischer Betreuer] Schulte, Axel [Gutachter] Schulte, and Jon [Gutachter] Platts. "Cooperation of Human and Artificial Intelligence on the Planning and Execution of Manned-Unmanned Teaming Missions in the Military Helicopter Domain : Concept, Requirements, Design, Validation / Ruben Strenzke ; Gutachter: Axel Schulte, Jon Platts ; Akademischer Betreuer: Axel Schulte ; Universität der Bundeswehr München, Fakultät für Luft- und Raumfahrttechnik." Neubiberg : Universitätsbibliothek der Universität der Bundeswehr München, 2019. http://d-nb.info/1205320113/34.

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32

Chen, Yen-Shi, and 陳彥熹. "AUTONOMOUS HOVER OF UNMANNED HELICOPTERS." Thesis, 2008. http://ndltd.ncl.edu.tw/handle/96467179674016754410.

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碩士<br>淡江大學<br>航空太空工程學系碩士班<br>96<br>The autonomous hover of unmanned helicopters and design of controllers are presented in this thesis. A Thunder Tiger Raptor-90 helicopter (renamed as H-Ling) is selected to investigate. Starting from the identi ed model of H-Ling we design proportional-integralderivative (PID) controllers to stabilize its attitude in hover. Although the general dynamics of a helicopter is highly coupled and nonlinear, for the purpose of implementation we here only discuss control of dynamics of four main channels, cyclic lateral input to rolling rate, cyclic longitudinal inpu
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33

"Modeling, state estimation and control of unmanned helicopters." 2012. http://library.cuhk.edu.hk/record=b5549553.

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無人直昇機是指在沒有搭載駕駛員下，能自動飛行的直昇機。這種飛行器除了不用令駕駛員冒上性命風險，亦由於其獨特飛行能力，例如空中旋停、急彎打轉等，令無人直昇機在執行危險任務上有著重要的優勢。但同時，由於沒有了駕駛員的關係，這種飛行器持續面對著一系列的技術難點。當中包括：（一）在飛行上，無人直昇機帶有一種未能確解的動態反應，偶合在主控軸上，令動態變化的預測變得困難；（二）絶大部份無人直昇機的導航倚賴全球定位儀，但這種定位儀卻極易受干擾，影響飛行安全；（三）由於每次任務的需要，機上搭載物的位置及多寡令飛行器上的重力分佈經常改變，令自動控制器需面密集的手動調度及系統識別。<br>對於無人直昇機的動態模型建構，我們提出了一種新辦法令過往未能確解的偶合動態反應，能被準確的量化及分析，因而使這種模型能更準確預測無人直昇機的動態變化。我們的辦法針對過往一種普遍使用但不能預測偶合動態反應，名為「遲相」的模型方法，並提出以主旋槳上的陀螺現像，去描述無人直昇機上的偶合動態反應。另外，我們的模型分析顯示出準確預測無人直昇機的動態反應需要識別一系列難以度測而又經常變化的系統參數，因此我們提出以一個相對隱性模型的辦法對解決往後有關導航及控制的問題更有利。<br>有關無人直昇機的導航，我們提出以慣性感測器去補償全球定位儀因干擾及訊號異常導致的感測數據中斷。通過一系列的噪音處理，我們的辦法能從慣性感測器的加速度讀數
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34

Wang, Jen-Chung, and 王忍忠. "Intelligent Distributed Formation Control of Small-Size Unmanned Helicopters." Thesis, 2016. http://ndltd.ncl.edu.tw/handle/teef42.

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博士<br>國立中興大學<br>電機工程學系所<br>104<br>This dissertation presents a distributed formation control system frame for a team of multiple small-size unmanned helicopters (SSUHs) flying together over complicated environments with static and dynamic obstacles, in order to achieve not only for formation keeping but also for collision-free contour trajectory tracking and contour flight. To synthesize the overall formation control system, the main research topics of the dissertation are classified into three core techniques. First, an intelligent adaptive trajectory tracking control method using fuzzy basis
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35

Jen-ChuanLiang and 梁仁銓. "The Research of Application Intermeshing Rotors on Unmanned Helicopters." Thesis, 2018. http://ndltd.ncl.edu.tw/handle/3q9pbc.

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碩士<br>國立成功大學<br>航空太空工程學系<br>106<br>The purpose of this study is to investigate the application of intermeshing rotors unmanned helicopters, including calculating the interference-induced power factor of intermeshing rotors, and inquiring design characteristics of intermeshing rotors. Three aspects are chosen to explore intermeshing rotors’ feature, i.e., interference-induced power factor, appearance, and application of unmanned helicopters. The design of the Kaman Aircraft's K-1200(K-MAX) and Kaman Aircraft’s HH-43B(Huskie) were applied to unmanned helicopters. The rotors shaft angle and the r
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36

Wang, Chi-Ruei, and 王啟叡. "Design of a Rotor Speed Control System for Unmanned Helicopters." Thesis, 2006. http://ndltd.ncl.edu.tw/handle/558296.

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碩士<br>國立臺北科技大學<br>車輛工程系所<br>94<br>As the unmanned helicopter advances in technology, the built-in avionics system for helicopters has become more complicated, and the cost has increased correspondingly. However, the external airflow interaction is very complicated, as the rotor speed becomes unstable, it will also affect the lift of the main rotor blades. It could cause minor disruption to the helicopter and become unstable; on another hand, it could put the fuselage and the control system in danger, or even cause destruction. In order to improve the safety of unmanned helicopter, we will focu
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Wang, Chin-Hsiung, and 王進雄. "Design of Test Platform and Hovering Control for Unmanned Helicopters." Thesis, 2010. http://ndltd.ncl.edu.tw/handle/99463548833687743460.

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碩士<br>國立屏東科技大學<br>車輛工程系所<br>98<br>A remote-control helicopter has six degrees of freedom and its dynamics is very nonlinear, which make the design of its controller very complicated. Without an autopilot, it is not easy to control an RC helicopter and crash may happen if an improper action is taken. In this research, a fuzzy controller is developed to do the hovering control of the helicopter. The controller design is validated by computer simulations and experimental tests on a platform. The simulations have been done under MATLAB/SIMULINK environment. The experimental tests were exercised
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38

Tang, Chien-Huai, and 唐鍵淮. "GPS Guided Positioning and Multi-Point Surveillance Control of Autonomous Unmanned Helicopters." Thesis, 2010. http://ndltd.ncl.edu.tw/handle/62998785879468275944.

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碩士<br>雲林科技大學<br>電機工程系碩士班<br>98<br>To realize autonomous flight on an unmanned aerial helicopter, this thesis have accomplished the four major objectives: (1) modification of controller gains for the new gasoline vehicle to meet a stable flight requirement; (2) reducing the time required for the design of the trim parameters by catching the expert-setting during the pilot mode and downloading the parameter values to the controller right after the auto mode has been switched; (3) extending the effective communication distance by replacing the wireless networks with RF modules; (4) achieving the
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Lu, Jian-han, and 呂建漢. "Sensorless Variable Speed Control of Brushless DC Motors for Electric Unmanned Helicopters." Thesis, 2007. http://ndltd.ncl.edu.tw/handle/15478281192700190107.

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碩士<br>國立雲林科技大學<br>電機工程系碩士班<br>95<br>Unmanned helicopters driven by oil engines have some drawbacks than those driven by electric motors such as high-cost maintenance, oil leak and shaking etc. Electric unmanned helicopters, which use brushless DC motors as power driving source of propellers, have become more and more popular nowadays because they are cost-effective and easier to maneuver. Conventionally, brushless DC Motors are driven by using hall sensors and non-contact commutation circuits and have the merits of low noise, long life, high efficiency, and easy maintenance. Instead of using h
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Hung, Wen-Lung, and 洪文龍. "The Development of a Landing/Takeoff and Hovering Control Augmentation System for Unmanned Helicopters." Thesis, 2008. http://ndltd.ncl.edu.tw/handle/vz26f8.

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Hsu, Fu-Jen, and 許甫任. "Platform Establishment for Sensorless Control Method of Brushless DC Motors applied to Dual-Axis Unmanned Helicopters." Thesis, 2014. http://ndltd.ncl.edu.tw/handle/98065273310613658179.

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碩士<br>國立交通大學<br>機械工程系所<br>102<br>Unmanned helicopter is usually driven by two types of power source, electric and fuel. Electrical remote control helicopter presents many advantages, including ease of maintenance, high energy conversion efficiency, low vibration, less weight and ease of control in aircraft attitude, along with many others, and is gradually becoming the primary choice of driving method. In the near future, unmanned remote control helicopter will replace costly manpower in low sophisticated air missions (such as aerial photography, small area cruise). In this paper, we use a hig
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"The nonlinear modelling and model predictive control of a miniature helicopter UAV." Thesis, 2012. http://hdl.handle.net/10210/5362.

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M.Ing.<br>Linear control system theory is well developed and has lead to a number of control system types with well-defined design methods that can be applied to any linear system. Unfortunately, no system in nature is truly linear. As a result, such non-linear systems must be represented by a linear model that is accurate over some region of the operating states of the system. The success of linear control theory in commercial applications is testament to the fact that some types of systems can be adequately represented by a linear model. However, systems with time-varying dynamics or non-lin
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Li, Chih-Chieh, and 李志傑. "Hovering Control for Unmanned Helicopter." Thesis, 2006. http://ndltd.ncl.edu.tw/handle/51574575996469403424.

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碩士<br>元智大學<br>機械工程學系<br>94<br>The aim of the thesis is to implement a flight control system for a unmanned helicopter (UAH). is the control system integrates a ultrasonic sensor, an accelerator, an compass, gyros…etc. The multi-input and multi-output flight control system for helicopter includes the following functions: 1.Flight heading control 2.Flight pitch and heave control 3.Flight attitude control When the unmanned helicopter starts to flight, a ground station monitors and sends commands through a wireless network. The complete unmanned helicopter includes two sub-systems: an attitude
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Chang, Li-Teng, and 張儷騰. "Embedded Control System for Unmanned Helicopter." Thesis, 2008. http://ndltd.ncl.edu.tw/handle/03170792339845253457.

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碩士<br>元智大學<br>機械工程學系<br>96<br>In this paper we were designed the avionics for UAH, and combined PIC controller with PC104 single board computer. The PIC controller was developed by C code. The PIC controller has integrated all of UAH sensors, and controlled RC servomotors. The single board computer was developed by Matlab xPC Target and Matlab Simulink. The single board computer has designed controller for UAH. The PIC controller had include for the following functions. - 6 channels PWM R/C servo output; - R/C Receiver signal decoding;. - Integrated IMU consisting of 3-axis gyro and 3-axis ac
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Yang, Chang-Pu, and 楊長圃. "Inertial Navigation System for Unmanned Helicopter." Thesis, 2004. http://ndltd.ncl.edu.tw/handle/88588908646585278617.

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碩士<br>元智大學<br>機械工程學系<br>92<br>We fulfill inertial navigation system for unmanned helicopter to collect flying speed, attitude, rotation, position, and azimuth. Inertial navigation system for unmanned helicopter includes attitude and heading reference system (AHRS) and inertial navigation system/global positioning system (INS/GPS). Kalman filter integrate GPS, compass, 3D accelerometer, and micro gyroscope. GPS can tell the absolute coordinate of position and the speed of object. Compass indicates the azimuth with magnetic flow. We propose the quaternion model to calcula
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Tseng, Yi-Chih, and 曾奕智. "SIMULATION OF DYNAMICS OF UNMANNED AERIAL HELICOPTER." Thesis, 2009. http://ndltd.ncl.edu.tw/handle/38610227126786512367.

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碩士<br>淡江大學<br>航空太空工程學系碩士班<br>97<br>In this paper we are going to develop a parameterized model for a small-scale unmanned helicopter H-Ling (a Thunder Tiger Raptor-90) and its identification using various techniques, including ARX, CIFER and PEM. The ultimate goal of this project is to extend the current work to build a fully functional autonomous rotorcraft. The equations of motion of a small-scaled rotorcraft are briefly reviewed first. We then briefly introduce the mathematics of ARX and PEM. With the flight test data, we obtain the identified parameters of the dynamical model.Numerical sim
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Raol, Divyarajsinh. "Vertical Control of Unmanned Helicopter During Payload Drop." 2015. http://hdl.handle.net/1993/30285.

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Unmanned helicopters in recent years have gained much attention due to their potential in both civil as well as military applications. Helicopter is an inherently unstable system. As a result there is a growing need of developing a control structure that allows the helicopter to perform various applications while remaining stable throughout the flight. This thesis presents developments of a robust controller for the vertical channel of an unmanned helicopter while carrying and dropping a payload. In addition, a simulation platform is developed in Simulink that uses a nonlinear six degree of f
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Lyu, Wei-Cheng, and 呂維誠. "Yaw rate control of Small Unmanned flybarless Helicopter." Thesis, 2017. http://ndltd.ncl.edu.tw/handle/67ztnu.

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碩士<br>元智大學<br>機械工程學系<br>105<br>Unmanned Aerial Helicopter, UAH, with strong flexibility, it can hover or turn round at the same position, also require deployed for missions only with very small take-off and landing area. In the near future, people attach importance to research, military mission and detect on UAH. The purpose of this research is build a yaw rate control system for small flybarless helicopter. Using the flight computer made by Yuan Ze University LAB 3425. The experiment used the commercially available heading lock gyro compensator to do flight test and collect data, build a heli
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Liu, Zhe-Jun, and 劉哲鈞. "Modeling and Parameter Identification of an Unmanned Helicopter." Thesis, 2005. http://ndltd.ncl.edu.tw/handle/vn82t4.

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碩士<br>國立臺北科技大學<br>機電整合研究所<br>94<br>The domestic unmanned helicopter development and research have founded on the aerodynamics and System and Parameter Identification of the vehicles. The goal of this study is building the mathematic model of an unmanned helicopter. Most of UAV modeling development in Taiwan have adopted the System and Parameter Identification of the vehicles to analyze and develop the related parameters. However, not all details and parameters can be obtained. This drawback has motivated the present study to develop a more realistic model for the rotary-wing UAV. This present
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Tseng, Jen-Hung, and 曾仁宏. "System Identification of Unmanned Helicopter: Applications to R-90." Thesis, 2007. http://ndltd.ncl.edu.tw/handle/85597508275134117370.

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碩士<br>淡江大學<br>航空太空工程學系博士班<br>95<br>The development of a parameterized model for a small-scale unmanned helicopter “H-ling” (a Thunder Tiger Raptor-90) and its identification using a frequency domain identification technique are described in this thesis. The construction of the R-90 dynamics using system ID techniques in this work is for potential applications to the control of autonomous hovering. Taking into consideration the future controller design, we adopt transfer functions of main channels as our dynamics model that explicitly accounts for the stabilizer bar, which has a strong influenc
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