This thesis is a study of modelling and control of a multirotor unmanned aerial vehicle(UAV). On behalf of Intuitive Aerial, a model of their hexarotor aircraft has been developedas a tool in further development and testing of their product. The potential of using ModelPredictive Control (MPC) as control method for multirotor UAV:s has also been evaluated.The model was successfully implemented in MATLAB/Simulink, as was the Model Predic-tive Controller. Quaternion angle representation has been used to avoid singularities in themodel and non-linear dynamics have been included in the simulation model. Unknownmodel parameters have been estimated with data acquired from testing. Model validity hasalso been evaluated with flight data gathered from flights using a test vehicle. A basic MPCformulation has been expanded to include reference tracking, integral action and to ensurestability.Assessment proved the model to be feasible but in need of more rigorous evaluation to guar-antee good performance. The MPC controller showed promising performance compared toa linear feedback controller.

This master's thesis has been on modeling, identification and control of a hexarotor system. It has been carried out on behalf of UAS Europe in Link\"{o}ping. A set of non-linear dynamic equations describing the motion of the hexarotor were derived. These equations were then implemented in Matlab/Simulink, which became a good simulation environment for further studies. A decentralized control system using P-PD controllers was successfully implemented in both simulation and on a hexarotor platform. The non-linear simulation model and the hexarotor platform were then identified using black box identification between virtual controls and angular rates. The result from identification of the hexarotor platform was not bad at all, but left some room for improvements. These linear models ware then used to tune the parameters of the inner PD controllers using a method called placement of dominant poles. This method worked well in simulation environment but unfortunately not as well on the real platform.

The use and practical applications of small UAV systems has continually grown in the past several years in both the public and private sectors. These UAV systems are used for not only defensive purposes, but for commercial applications such as exterior bridge and home inspections, wildlife/wildfire management and observation, conservation exercises, law-enforcement, radio-repeating operations, and a wide variety of other uses that may not warrant the use, expense, space constraints, or risk of a manned aircraft. This thesis focuses on the design of a fixed pitch multirotor UAV system for use in furthering research projects and facilitating payload data collection from a flying platform without the expense or risk of testing with available larger UAV systems. The design of a multirotor UAV system with a flight control scheme, communication architecture and hardware, electrical architecture and hardware, and mechanical design is presented. An Extended Kalman Filter (EKF) strategy is implemented aboard a developed Inertial Measurement Unit (IMU) to estimate vehicle state. Experiments then validated the estimates from the EKF through a comparative approach between the developed unit and a commercial unit. A nonlinear flight control system is implemented based on an Integral-Backstepping control strategy. The flight control strategy was then fully simulated and exhaustively tested under a variety of external disturbances and initial conditions from a fully dynamic modeled environment. Parameters about the vehicle were experimentally determined to increase the accuracy of the model which would increase the chances of successful flight operations. Flight demonstrations were conducted to evaluate the abilities and performance of the control system, along with testing the interface abilities and reliability between a universal ground control station (UGCS) and the aircraft. Lastly, the model was revisited with the input data from the flight control experiment and the output captured was evaluated against the output of the model system to evaluate effectiveness, reliability, and accuracy of the model. The results of the comparison showed that the computer simulation was accurate in predicting attitude and altitude of the vehicle to that of the realized system. / Master of Science

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Scaffolding and videoprojection on the gallery floor act like challenge to watch videos from the right focus – from the top of the safoolding. Instalation should mostly force the audience to get in touch with situation, which is unbearable for someone, who is scared from the heights – acrophobic.

This thesis deals with increasing the safety of the external perimeter. The theoretical part describes the parameters of areas exhibiting an increased safety risk. For these spaces, relevant safety hazards and corresponding elimination methods are determined. Then, the term "drone" is analyzed in the context of its applicability. The practical section characterizes the process of building and configuring unmanned aircraft to guard the perimeter and the designing and fabrication of an automatic charging station for the aircraft. The final part of the thesis is a brief manual describing correct handling of the created system.

Submitted by Renata Lopes (renatasil82@gmail.com) on 2017-04-25T17:55:23Z No. of bitstreams: 1 murilloferreiradossantos.pdf: 10926905 bytes, checksum: fd28a8c6e03bce5e40e5620a6bbf1666 (MD5) / Approved for entry into archive by Adriana Oliveira (adriana.oliveira@ufjf.edu.br) on 2017-04-26T12:22:42Z (GMT) No. of bitstreams: 1 murilloferreiradossantos.pdf: 10926905 bytes, checksum: fd28a8c6e03bce5e40e5620a6bbf1666 (MD5) / Made available in DSpace on 2017-04-26T12:22:42Z (GMT). No. of bitstreams: 1 murilloferreiradossantos.pdf: 10926905 bytes, checksum: fd28a8c6e03bce5e40e5620a6bbf1666 (MD5) Previous issue date: 2014-07-30 / Este trabalho tem o objetivo de desenvolver o controle tolerante a falhas de um sistema de propulsão de hexacópteros, visando mante-lo em condições de voo. Inicialmente, apresenta-se a modelagem do sistema, abordando o modelo cinemático e dinâmico da aeronave para a simulação e controle do sistema onde as forças gravitacionais e de propulsão são consideradas. Falhas nos sistemas de propulsão são inseridas para que quando detectadas, o sistema seja operado com outra sintonia de controladores PID, mantendo-o em condições de voo. Por fim, os resultados são simulados e analisados onde através dos índices de desempenho IAE, ISE e ITSE seja possível realizar um estudo de viabilidade do tempo limite que uma técnica de detecção e identificação de falhas terá disponível para localizar qual sistema de propulsão se encontra com problemas. Os resultados foram satisfatórios mostrando ser uma técnica possível de se implementada na aeronave desenvolvida. / This dissertation aims to develop the fault tolerant control of a propulsion system of hexacopters, which intends to keep it in good flight conditions. Initially, it’s presented the modeling of the system, considering the kinematic and dynamic model of the aircraft where the gravitational and propulsion forces are considered. Failures in propulsion systems are inserted to the system and when detected, the system can be operated with the new PID tuning, keeping it in flight. Finally, the results are simulated and analyzed using performance indices as IAE, ISE and ITSE, making possible to perform the feasibility study of the time limit that a technique for detecting and identifying faults have available to find which propulsion system meets problems. The results were satisfactory showing to be a possible technique to be implemented in the aircraft developed.

This thesis focuses on the design of the hexacopter construction for photographic purposes with maximum load of 4 kg. When constructing a hexacopter it is necessary to take into account a number of factors. For the actual construction the correct dimensioning of the supporting frame is important as well as the locomotor system. The main concept of this thesis includes three-axis gimbal for camera control. The verification of the structure strength was performed using FEM analysis. This work describes also the selection of individual components and their wiring. The end is dedicated to safety and different procedures for reducing operation risks.