A simulation tool for flight dynamics and control investigations of three different Vertical Take Off and Landing (VTOL) unmanned aircraft configurations has been developed. A control concept has been proposed in order to take advantage of the fast response characteristics of the ordinary small engine/propeller propulsion systems in such aircraft, as well as replacing the complex rotors used previously in VTOL concepts for small unmanned aircraft. The simulation model has been established on the basis of the proposed concept so that it can also be used to study the feasibility of this idea. An Object-based methodology has been introduced so as to reduce the amount of aerodynamic required data for the simulation model. The equations of motion associated with the aircraft multibody system with ten degrees of freedom have been derived using the Newton-Euler method. The modelling of various subsystems including the propeller model, the airframe aerodynamics and the engine model has been carried out. A method for calculating the propellers' slipstream effects on the other components has been presented. Input data for the simulation model have been estimated, using different sources. The Advanced Continuous Simulation Language (ACSL) has been used for the programming of the mathematical model. A series of comprehensive tests have been carried out in order to demonstrate the validity of the simulation model. The ability of the simulation model to explain the aircraft modes of motion as well as to discover unknown nonlinear behaviours and to describe them has been demonstrated.

A combined wing and propeller model is presented as a low-cost approach to preliminary modeling of slipstream effects on a finite wing. The wing aerodynamic model employs a numerical lifting-line method utilizing the 3D vortex lifting law along with known 2D airfoil data to predict the lift distribution across a wing for a prescribed upstream flowfield. The propeller/slipstream model uses blade element theory combined with momentum conservation equations. This model is expected to be of significant importance in the design of tail-sitter vertical take-off and landing (VTOL) aircraft, where the propeller slipstream is the primary source of air flow past the wings in some flight conditions. The algorithm is presented, and results compared with published experimental data.

<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 using only the GPS. Therefore, a vision system using a camera anda pattern provided landing platform has been developed. The vision system givesaccurate measurement of the 6-DOF pose of the helicopter relative the platform.These measurements are used to guide the helicopter to the landing target. Inorder to use the vision system in real time, fast image processing algorithms havebeen developed. The vision system can easily match up the with the camera framerate of 30 Hz.</p> / <p>Ett kontrolsystem för att autonomt landa en modellhelikopter har utvecklats.Mätdata från en GPS, en kamera samt en kompass fusioneras med ett Extend-ed Kalman Filter för tillståndsestimering av helikoptern. Fyra PID-regulatorer,en för varje kontrolsignal på helikoptern, har används för regleringen. Under densista provflygningen gjordes tre landingar av vilken den minst lyckade slutade35 cm från målet.    På grund av en drift i GPS-mätningarna är det omöjligt att landa helikopternmed hög precision med bara en GPS. Därför har ett bildbehandlingssystem som an-vänder en kamera samt ett mönster på platformen utvecklats. Bidbehandlingssys-temet mäter positionen och orienteringen av helikoptern relativt platformen. Dessamätningar används kompensera för GPS-mätningarnas drift. Snabba bildbehan-dlingsalgoritmer har utvecklats för att kunna använda bildbehandlingssystemet irealtid. Systemet är mycket snabbare än 30 bilder per sekund vilket är kameranshastighet.</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 using only the GPS. Therefore, a vision system using a camera anda pattern provided landing platform has been developed. The vision system givesaccurate measurement of the 6-DOF pose of the helicopter relative the platform.These measurements are used to guide the helicopter to the landing target. Inorder to use the vision system in real time, fast image processing algorithms havebeen developed. The vision system can easily match up the with the camera framerate of 30 Hz. / Ett kontrolsystem för att autonomt landa en modellhelikopter har utvecklats.Mätdata från en GPS, en kamera samt en kompass fusioneras med ett Extend-ed Kalman Filter för tillståndsestimering av helikoptern. Fyra PID-regulatorer,en för varje kontrolsignal på helikoptern, har används för regleringen. Under densista provflygningen gjordes tre landingar av vilken den minst lyckade slutade35 cm från målet.    På grund av en drift i GPS-mätningarna är det omöjligt att landa helikopternmed hög precision med bara en GPS. Därför har ett bildbehandlingssystem som an-vänder en kamera samt ett mönster på platformen utvecklats. Bidbehandlingssys-temet mäter positionen och orienteringen av helikoptern relativt platformen. Dessamätningar används kompensera för GPS-mätningarnas drift. Snabba bildbehan-dlingsalgoritmer har utvecklats för att kunna använda bildbehandlingssystemet irealtid. Systemet är mycket snabbare än 30 bilder per sekund vilket är kameranshastighet.

abstract: The objective of this work is to develop a Stop-Rotor Multimode UAV. This UAV is capable of vertical take-off and landing like a helicopter and can convert from a helicopter mode to an airplane mode in mid-flight. Thus, this UAV can hover as a helicopter and achieve high mission range of an airplane. The stop-rotor concept implies that in mid-flight the lift generating helicopter rotor stops and rotates the blades into airplane wings. The thrust in airplane mode is then provided by a pusher propeller. The aircraft configuration presents unique challenges in flight dynamics, modeling and control. In this thesis a mathematical model along with the design and simulations of a hover control will be presented. In addition, the discussion of the performance in fixed-wing flight, and the autopilot architecture of the UAV will be presented. Also presented, are some experimental "conversion" results where the Stop-Rotor aircraft was dropped from a hot air balloon and performed a successful conversion from helicopter to airplane mode. / Dissertation/Thesis / M.S.Tech Mechanical Engineering 2011

Airborne Wind Energy Systems (AWES) harness the power of high-altitude winds using tethered planes or kites. Continuous and reliable operation requires that AWES become autonomous devices, but the wind intermittency forces the system to repeatedly take-off to start, and land to shut-off. Therefore, a common approach to facilitate the operation is implementing Vertical take-off and landing (VTOL) functionality. This thesis models and simulates AWES flights working towards the implementation of flight controller hardware and autonomous operation of an AWES demonstrator platform. The Ardupilot open-source autopilot platform provides a convenient tool for modeling, simulation, and hardware implementation of small-scale airplanes. An AWES lab-scale demonstrator was developed to obtain operational insight, get preliminary flight data, and real-world experience in this technology. A quadplane was developed by combining a structurally reinforced glider with VTOL and autopilot components. Its performance is obtained from static and aerodynamic studies and converted into the Ardupilot parameter format to define it in the simulation. An AWES flight model was developed from the ground up to evaluate the performance of a simple flight controller in trajectory tracking. The Ardupilot Software-in-Loop (SIL) tool expands the simulation capabilities by running the flight controller code without requiring any hardware. This allowed controller tuning and flight plan evaluation with a more advanced fight model. AWES crosswind flight simulation was only possible due to the incorporation of an elastic tether and an ideal winch into the physics model. As a result, different trajectories and configurations were tested to find the optimal parameters that were uploaded to the flight controller board. The operational capabilities of the AWES demonstrator were expanded with a flight testing campaign. By targeting individual objectives, each test gradually increased its complexity and ensured that the flight envelope was safely expanded. The results were validated with the simulation before moving on to the next flight test. The testing campaign is still underway due to challenges and limitations presented by the legal and logistical aspects of operating the quadplane. However, preliminary flight tests in VTOL mode have been completed and were consistent with the simulated results in terms of autonomous waypoint navigation and attitude control. / Graduate

The use of magnetometers combined with unmanned aerial vehicles (UAVs) is an emerging market for commercial and military applications. This study presents the methodology used to magnetically characterize a novel fixed-wing vertical take-off and landing (VTOL) UAV. The most challenging aspect of integrating magnetometers on manned or unmanned aircraft is minimizing the amount of magnetic noise generated by the aircraft’s onboard components. As magnetometer technology has improved in recent years magnetometer payloads have decreased in size. As a result, there has been an increase in opportunities to employ small to medium UAV with magnetometer applications. However, in comparison to manned aviation, small UAVs have smaller distance scales between sources of interference and sensors. Therefore, more robust magnetic characterization techniques are required specifically for UAVs. This characterization determined the most suitable position for the magnetometer payload by evaluating the aircraft’s static-field magnetic signature. For each aircraft component, the permanent and induced magnetic dipole moment characteristics were determined experimentally. These dipole characteristics were used to build three dimensional magnetic models of the aircraft. By assembling the dipoles in 3D space, analytical and numerical static-field solutions were obtained using MATLAB computational and COMSOL finite element analysis frameworks. Finally, Tolles and Lawson aeromagnetic compensation coefficients were computed and compared to evaluate the maneuver noise for various payload locations. The magnetic models were used to study the sensitivity of the aircraft configuration and to simultaneously predict the effects at potential sensor locations. The study concluded by predicting that a wingtip location was the area of lowest magnetic interference. / Graduate

[ES] Los Vehículos Aéreos no Tripulados (o drones) ya han demostrado su utilidad en una gran variedad de aplicaciones. Hoy en día, se utilizan para fotografía, cinematografía, inspecciones y vigilancia, entre otros. Sin embargo, en la mayoría de los casos todavía son controlados por un piloto, que como máximo suele estar volando un solo dron cada vez. En esta tesis, tratamos de avanzar en paso más allá en esta tecnología al permitir que múltiples drones con capacidad para despegue y aterrizaje vertical trabajen de forma sincronizada, como una sola entidad. La principal ventaja de realizar vuelos en grupo, comúnmente denominado enjambre, es que se pueden realizar tareas más complejas que utilizando un solo dron. De hecho, un enjambre permite cubrir más área en el mismo tiempo, ser más resistente, tener una capacidad de carga más alta, etc. Esto puede habilitar el uso de nuevas aplicaciones, o una mejor eficiencia para las aplicaciones existentes. Sin embargo, una parte clave es que los miembros del enjambre deben organizarse correctamente, ya que, durante el vuelo, diferentes perturbaciones pueden provocar que sea complicado mantener el enjambre como una unidad coherente. Una vez que se pierde esta coherencia, todos los beneficios previamente mencionados de un enjambre se pierden también. Incluso, aumenta el riesgo de colisiones entre los elementos del enjambre. Por lo tanto, esta tesis se centra en resolver algunos de estos problemas, proporcionando un conjunto de algoritmos que permitan a otros desarrolladores crear aplicaciones de enjambres de drones. Para desarrollar los algoritmos propuestos hemos incorporado mejoras al llamado ArduSim. Este simulador nos permite simular tanto la física de un dron como la comunicación entre drones con un alto grado de precisión. ArduSim nos permite implementar protocolos y algoritmos (bien probados) en drones reales con facilidad. Durante toda la tesis, ArduSim ha sido utilizado ampliamente. Su utilización ha permitido que las pruebas fueran seguras, y al mismo tiempo nos permitió ahorrar mucho tiempo, dinero y esfuerzo de investigación. Comenzamos nuestra investigación sobre enjambres asignando posiciones aéreas para cada dron en el suelo. Suponiendo que los drones están ubicados aleatoriamente en el suelo, y que necesitan alcanzar una formación aérea deseada, buscamos una solución que minimice la distancia total recorrida por todos los drones. Para ello se empezó con un método de fuerza bruta, pero rápidamente nos dimos cuenta de que, dada su alta complejidad, este método funciona mal cuando el número de drones aumenta. Por lo tanto, propusimos una heurística. Como en todas las heurísticas, se realizó un compromiso entre complejidad y precisión. Al simplificar el problema, encontramos que nuestra heurística era capaz de calcular una solución muy rápidamente sin aumentar sustancialmente la distancia total recorrida. Además, implementamos el algoritmo de Kuhn-Munkres (KMA), un algoritmo que ha demostrado proporcionar la respuesta exacta (es decir, reducir la distancia total recorrida) en el menor tiempo posible. Después de muchos experimentos, llegamos a la conclusión de que nuestra heurística es más rápida, pero que la solución proporcionada por el KMA es ligeramente más eficiente. En particular, aunque la diferencia en la distancia total recorrida es pequeña, el uso de KMA reduce el número de trayectorias de vuelo que se cruzan entre sí, lo cual es una métrica importante para las siguientes propuestas.[...] / [CA] Els vehicles aeris no tripulats (o drons) ja han demostrat la seua utilitat en una gran varietat d'aplicacions. Avui dia, s'utilitzen per a fotografia, cinematografia, inspeccions i vigilància, entre altres. No obstant això, en la majoria dels casos encara són controlats per un pilot, que com a màxim sol controlar el vol d'un sol dron cada vegada. En aquesta tesi, tractem d'avançar un pas més enllà en aquesta tecnologia, en permetre que múltiples drons amb capacitat per a l'enlairament i l'aterratge vertical treballen de forma sincronitzada, com una sola entitat. El principal avantatge de realitzar vols en grup, comunament denominats eixam, és que es poden fer tasques més complexes que utilitzant un sol dron. De fet, un eixam permet cobrir més àrea en el mateix temps, ser més resistent, tenir una capacitat de càrrega més alta, etc. Això pot habilitar l'ús de noves aplicacions, o una millor eficiència per a les aplicacions existents. No obstant això, una punt clau és que els membres de l'eixam han d'organitzar-se correctament, ja que, durant el vol, diferents pertorbacions poden provocar que siga complicat mantenir l'eixam com una unitat coherent. Una vegada que es perd aquesta coherència, tots els beneficis prèviament esmentats d'un eixam es perden també. Fins i tot, augmenta el risc de col·lisions entre els elements de l'eixam. Per tant, aquesta tesi se centra a resoldre alguns d'aquests problemes, proporcionant un conjunt d'algorismes que permeten a altres desenvolupadors crear aplicacions d'eixams de drons. Per a desenvolupar els algorismes proposats hem incorporat millores a l'anomenat ArduSim. Aquest simulador ens permet simular tant la física d'un dron com la comunicació entre drons amb un alt grau de precisió. ArduSim ens permet implementar protocols i algorismes (ben provats) en drons reals amb facilitat. Durant tota la tesi, ArduSim s'ha utilitzat àmpliament. El seu ús ha permès que les proves foren segures, i al mateix temps ens va permetre estalviar molt de temps, diners i esforç d'investigació. Per tant, es va utilitzar ArduSim per a cada bloc de construcció que vam desenvolupar. Comencem la nostra recerca sobre eixams assignant posicions aèries per a cada dron en terra. Suposant que els drons estan situats aleatòriament en terra i que necessiten assolir la formació aèria desitjada, cerquem una solució que minimitze la distància total recorreguda per tots els drons. Per a això, es va començar amb un mètode de força bruta, però ràpidament ens vam adonar que, atesa l'alta complexitat, aquest mètode funciona malament quan el nombre de drons augmenta. Per tant, vam proposar una heurística. Com en totes les heurístiques, es va fer un compromís entre complexitat i precisió. En simplificar el problema, trobem que la nostra heurística era capaç de calcular una solució molt ràpidament sense augmentar substancialment la distància total recorreguda. A més, vam implementar l'algorisme de Kuhn-Munkres (KMA), un algorisme que ha demostrat proporcionar la resposta exacta (és a dir, reduir la distància total recorreguda) en el menor temps possible. Després de molts experiments, arribem a la conclusió que la nostra heurística és més ràpida, però que la solució proporcionada pel KMA és lleugerament més eficient. En particular, encara que la diferència en la distància total recorreguda és xicoteta, l'ús de KMA redueix el nombre de trajectòries de vol que s'encreuen entre si, la qual cosa és una mètrica important per a les propostes següents.[...] / [EN] Unmanned Aerial Vehicles (UAVs) have already proven to be useful in many different applications. Nowadays, they are used for photography, cinematography, inspections, and surveillance. However, in most cases they are still controlled by a pilot, who at most is flying one UAV at a time. In this thesis, we try to take this technology one step further by allowing multiple Vertical Take-off and Landing (VTOL) UAVs to work together as one entity. The main advantage of this group, commonly referred to as a swarm, is that it can perform more complex tasks than a single UAV. When organized correctly, a swarm allows for: more area to be covered in the same time, more resilience, higher load capability, etc. A swarm can lead to new applications, or a better efficiency for existing applications. A key part, however, is that they should be organized correctly. During the flight, different disturbances will make it complicated to keep the swarm as one coherent unit. Once this coherency is lost, all the previously mentioned benefits of a swarm are lost as well. Even worse, the chance of a hazard increases. Therefore, this thesis focuses on solving some of these issues by providing a baseline of building blocks that enable other developers to create UAV swarm applications. In order to develop these building blocks, we improve a multi-UAV simulator called ArduSim. This simulator allows us to simulate both the physics of a UAV, and the communication between UAVs with a high degree of accuracy. This is a crucial part because it allows us to deploy (well tested) protocols and algorithms on real UAVs with ease. During the entirety of this thesis, ArduSim has been used extensively. It made testing safe, and allowed us to save a lot of time, money and research effort. We started by assigning airborne positions for each UAV on the ground. Assuming that the UAVs, are placed randomly on the ground, and that they need to reach a desired aerial formation, we searched for a solution that minimizes the total distance travelled by all the UAVs. We started with a brute-force method, but quickly realized that, given its high complexity, this method performs badly when the number of UAVs grows. Hence, we created a heuristic. As for all heuristics, a trade-off was made between complexity and accuracy. By simplifying the problem, we found that our heuristic was able to calculate a solution very quickly without increasing the total distance travelled substantially. Furthermore, we implemented the \ac{KMA}, an algorithm that has been proven to provide the exact answer (i.e. minimal total distance travelled) in the shortest time possible. After many experiments, we came to the conclusion that our heuristic is faster, but that the solution provided by the \ac{KMA} is slightly better. In particular, although the difference in total distance travelled is small, the \ac{KMA} reduces the numbers of flight paths crossing each other, which is an important metric in our next building block. Once we developed algorithms to assign airborne positions to each UAV on the ground, we started developing algorithms to take off all those UAVs. The objective of these algorithms is to reduce the time it takes for all the UAVs to reach their aerial position, while ensuring that all UAVs maintain a safe distance. The easiest solution is a sequential take-off procedure, but this is also the slowest approach. Hence, we improved it by first proposing a semi-sequential and later a semi-simultaneous take-off procedure. With this semi-simultaneous take-off procedure, we are able to reduce the takeoff time drastically without introducing any risk to the aircraft. [..] / Wubben, J. (2023). Distributed management and coordination of UAV swarms based on infrastructureless wireless networks [Tesis doctoral]. Universitat Politècnica de València. https://doi.org/10.4995/Thesis/10251/198887