This thesis documents a research project in which an autonomous flight control system (FCS) was designed to control and navigate small, high-speed, unmanned, jet-turbine powered fixed-wing aircraft. The FCS was designed to allow the aircraft to maintain controlled flight, and return to a home location, without any operator intervention. The flight control computer was built with an FPGA, using a Microblaze soft-core microprocessor running the uClinux operating system. The configurable FPGA computing platform allowed flexibility for interfacing quickly with a wide range of sensors and control modules. A commercial inertial measurement unit was used for aircraft state estimation, and the flight control system was able to provide stability and precise flight-path control for multiple turbinepowered aircraft over the wide flight airspeed envelope these vehicles are capable of. In addition, the custom ground control station which provides an operator control interface for the FCS is discussed.

The last decade has seen significant advances in the development of Vertical takeoff and landing (VTOL) unmanned aerial vehicles (UAVs). The emergence of enabling technologies, in addition to the practical usefulness of such systems has driven their development to a point where numerous technology demonstrators and commercial products are now in existence. Of particular interest has been the development of small scale, VTOL UAVs commonly referred to as mini and micro-VTOL UAVs. The versatility and agility of such vehicles offers great potential for the use in clustered, urban environments. Despite recent advancements, the autonomous navigation of VTOL UAVs remains a very challenging research area. The dynamics of VTOL UAVs are heavily nonlinear, underactuated and non-minimum phase. This, coupled with the aggressive maneuvers that such vehicles are expected to execute provides a stimulating problem in dynamic control. This is particularly true in the case of micro-VTOL UAVs. The fast, nonlinear nature of these systems render classical, linear control approaches inadequate. The past twenty years has seen great interest in the development of nonlinear control strategies. This has led to the emergence of a number of standard design tools, most notably feedback linearisation and Lyapunov-based, backstepping approaches. Such design techniques offer a framework for the derivation of model based control laws capable of achieving global stabilisation and trajectory tracking control for heavily nonlinear systems. Recently, there has been significant interest in the application of such nonlinear control paradigms for the stabilisation and control of VTOL UAVs. The aim of this thesis is to further the application and analysis of nonlinear control design techniques for the control of VTOL UAVs. In particular, focus is placed on Lyapunov-based, backstepping-type control approaches. The first half of this thesis investigates Lyapunov-based control strategies that cast the closed-loop VTOL dynamics into a globally stable, cascade structure. This work was directly inspired by, and builds on, a variety of previously published works. Firstly, an alternative design approach to that previously published is presented, resulting in an improved closed-loop dynamic structure. Although inspired by the VTOL system, this idea may be generalised for the control of a broad class of systems, and is presented as such. A singularity issue arising in the cascade control of VTOL vehicles is then investigated, and a novel approach to overcome this issue is formulated. The second half of this thesis is dedicated to the trajectory tracking control of VTOL UAVs at velocities where the influence of aerodynamics is significant. In general, the aerodynamic models of VTOL UAVs are heavily nonlinear and poorly known. The use of such models in a backstepping framework that uses explicit differentiation of these models for dynamic inversion is questioned, due to the potential sensitivity of such nonlinear models. Consequently, an alternative approach utilising coupled filters to avoid such sensitivity issues is proposed. All control designs formulated in this thesis are accompanied by proofs guaranteeing their global stability, and numerical simulations demonstrating their time domain response characteristics. / http://library.adelaide.edu.au/cgi-bin/Pwebrecon.cgi?BBID=1298413 / Thesis (Ph.D.) -- University of Adelaide, School of Mechanical Engineering, 2007

The field of UAV systems is an active research area with potential for development and enhancement in various perspectives. This thesis investigates different issues related to the design, operation and control of UAV systems with a focus on the application side of each proposed solution where the implementation side and applicability of the proposed solutions are always considered with high priority. The thesis discusses unmodeled actuator dynamics and their effect on UAV systems when using feedback linearisation to linearize nonlinear models of UAVs. The analysis shows potential risk when implementing feedback linearisation and neglecting actuator dynamics even for first order actuator system. A solution algorithm of two stage feedback linearisation is proposed to handle actuator dynamics and linearize the main dynamics of the system. In the field of design and operation of UAVs, this thesis proposes a systematic design procedure for electric propulsion systems that are widely used in UAVs. The design procedure guides the designer step by step to achieve minimum propulsion system weight or maximum flight time or a trade off between the two factors from the supplied solution sets. On the navigation side, the thesis proposes a new indoor navigation system that is easy to implement and less costly compared with other indoor navigation systems. The proposed system can be classified under computer-vision based navigation systems, however, it needs less information and less computational capacity. The thesis also contributes to the structure design of UAV systems by producing a novel tri-rotor UAV platform. The proposed UAV is novel in structure and design and has a centralized control system that stabilizes and tracks both rotational and transitional motion of the vehicle simultaneously.

La plupart des applications des avions drones sont liées à l'observation d'événements au sol. En particulier, les suivi de cibles terrestres mobiles, qu'elles soient statiques, lentes ou rapides, est une tâche essentielle pour un drone. L'objectif global de la thèse est de proposer des méthodes qui permettent à un drone de suivre une cible terrestre, dans les conditions suivantes: - Le drone est de type voilure fixe équipé d'une caméra monoculaire. - Présence d'obstacles qui occultent la visibilité de zones au sol. - Existence de zones d'exclusion aérienne qui limitent le mouvement aérien. - Restrictions sur le champ de vue du capteur qui assure le suivi (caméra) - Différents comportements de la cible : elle peut évoluer librement ou sous contraintes dynamiques (cas d'une voiture par exemple), et peut être neutre ou évasive~: dans ce dernier cas, elle peut exploiter la présence d'obstacles pour éviter d'être perçue par le drone. Trois approches pour aborder ce problème sont proposées dans la thèse : - Une méthode basée aux lois de contrôle et de la navigation, - Une méthode basée sur la prédiction des déplacements de la cible, - Et une approche basée sur la théorie des jeux. Des résultats obtenus par des simulations réalistes et avec un drone sont présentés, pour évaluer et comparer les avantages et inconvénients de chacune des approches. Des extensions au cas "multi-drones" sont aussi proposées.

This thesis presents the design, modeling, and control of a fully-actuated multi-rotor unmanned aerial vehicle (UAV). Unlike conventional multi-rotors, which suffer from two degrees of underactuation in their propeller plane, the choice of an unconventional propeller configuration in the new drone leads to an even distribution of actuation across the entire force-torque space. This allows the vehicle to produce any arbitrary combination of forces and torques within a bounded magnitude and hence execute motion trajectories unattainable with conventional multi-rotor designs. This system, referred to as the \omninospace, decouples the position and attitude controllers, simplifying the motion control problem. Position control is achieved using a PID feedback loop with gravity compensation, while attitude control uses a cascade architecture where the inner loop follows an angular rate command set by the outer attitude control loop. A novel model is developed to capture the disturbance effects among interacting actuator airflows of the \omninospace. Given a desired actuator thrust, the model computes the required motor command using the current battery voltage and thrusts of disturbing actuators. A system identification is performed to justify the use of a linear approximation for parameters in the model to reduce its computational footprint in real-time implementation. The \omni benefits from two degrees of actuation redundancy resulting in a control allocation problem where feasible force-torques may be produced through an infinite number of actuator thrust combinations. A novel control allocation approach is formulated as a convex optimization to minimize the \omnis energy consumption subject to the propeller thrust limits. In addition to energy savings, this optimization provides fault tolerance in the scenario of a failed actuator. A functioning prototype of the \omni is built and instrumented. Experiments carried out with this prototype demonstrate the capabilities of the new drone and its control system in following various translational and rotational trajectories, some of which would not be possible with conventional multi-rotors. The proposed optimization-based control allocation helps reduce power consumption by as much as 6\%, while being able to operate the drone in the event of a propeller failure. / Thesis / Master of Applied Science (MASc)

Several configurations of Unmanned Aerial Vehicles (UAVs) were proposed to support different applications. One of them is the tailsitter, a fixed-wing aircraft that takes off and lands on its own tail, with the high endurance advantage from fixed-wing aircraft and, as helicopters and multicopters, not requiring a runway during takeoff and landing. However, a tailsitter has a complex operation with multiple flight stages, each one with its own particularities and requirements, which emphasises the necessity of a reliable autopilot for its use as a UAV. The literature already introduces tailsitter UAVs with complex mechanisms or with multiple counter-rotating propellers, but not one with only one propeller and without auxiliary structures to assist in the takeoff and landing. This thesis presents a tailsitter UAV, named AVALON (Autonomous VerticAL takeOff and laNding), and its autopilot, composed of 3 main units: Sensor Unit, Navigation Unit and Control Unit. In order to choose the most appropriate techniques for the autopilot, different solutions are evaluated. For Sensor Unit, Extended Kalman Filter and Unscented Kalman Filter estimate spatial information from multiple sensors data. Lookahead, Pure Pursuit and Line-of-Sight, Nonlinear Guidance Law and Vector Field path-following algorithms are extended to incorporate altitude information for Navigation Unit. In addition, a structure based on classical methods with decoupled Proportional-Integral-Derivative controllers is compared to a new control structure based on dynamic inversion. Together, all these techniques show the efficacy of AVALONs autopilot. Therefore, AVALON results in a small electric tailsitter UAV with a simple design, with only one propeller and without auxiliary structures to assist in the takeoff and landing, capable of executing all flight stages. / Diversas configurações de Veículos Aéreos Não Tripulados (VANTs) foram propostas para serem utilizadas em diferentes aplicações. Uma delas é o tailsitter, uma aeronave de asa fixa capaz de decolar e pousar sobre a própria cauda. Esse tipo de aeronave apresenta a vantagem de aeronaves de asa fixa de voar sobre grandes áreas com pouco tempo e bateria e, como helicópteros e multicópteros, não necessita de pista para decolar e pousar. Porém, um tailsitter possui uma operação complexa, com múltiplos estágios de voo, cada um com suas peculiaridades e requisitos, o que enfatiza a necessidade de um piloto automático confiável para seu uso como um VANT. A literatura já introduz VANTs tailsitters com mecanismos complexos ou múltiplos motores contra-rotativos, mas não com apenas um motor e sem estruturas para auxiliar no pouso e na decolagem. Essa tese apresenta um VANT tailsitter, chamado AVALON (Autonomous VerticAL takeOff and laNding), e seu piloto automático, composto por 3 unidades principais: Unidade Sensorial, Unidade de Navegação e Unidade de Controle. Diferentes soluções são avaliadas para a escolha das técnicas mais apropriadas para o piloto automático. Para a Unidade Sensorial, Extended Kalman Filter e Unscented Kalman Filter estimam a informação espacial de múltiplos dados de diversos sensores. Os algoritmos de seguimento de trajetória Lookahead, Pure Pursuit and Line-of-Sight, Nonlinear Guidance Law e Vector Field são estendidos para considerar a informação da altitude para a Unidade de Navegação. Além do mais, uma estrutura baseada em métodos clássicos com controladores Proporcional- Integral-Derivativo desacoplados é comparada a uma nova estrutura de controle baseada em dinâmica inversa. Juntas, todas essas técnicas demonstram a eficácia do piloto automático do AVALON. Portanto, AVALON resulta em um VANT tailsitter pequeno e elétrico, com um design simples, apenas um motor e sem estruturas para auxiliar o pouso e a decolagem, capaz de executar todos os estágios de voo.

Thesis (MScEng)--Stellenbosch University, 2013. / ENGLISH ABSTRACT: In this thesis the strategy for performing System Identification on an aircraft is presented. The ultimate aim of this document is to outline the steps required for successful aircraft parameter estimation within a Fault Tolerant Control Framework. A brief derivation of the classical 6 degree-of-freedom aircraft model is firstly presented. The derivation gives insight into the aircraft dynamics that are to be used to estimate the aircraft parameters, and provides a basis for the methods provided in this thesis. Different techniques of System Identification were evaluated, resulting in the choice of the Regression method to be used. This method, based on the Least-Squares method, is chosen because of its simplicity of use and because it does not require as much computational time as the other methods presented. Regression methods, including a recursive algorithm, are then applied to aircraft parameter estimation and practical considerations such as Identifiability and corrupted measurements are highlighted. The determination of unknown measurements required for System Identification of aircraft parameters is then discussed. Methods for both estimating and measuring the Angle-of-Attack (AoA) and angular accelerations are presented. The design and calibration of an AoA probe for AoA measurements, as well as a novel method that uses distributed sensors to determine the angular accelerations is also presented. The techniques presented in this thesis are then tested on a non-linear aircraft model. Through simulation it was shown that for the given sensor setup, the methods do not provide sufficiently accurate parameter estimates. When using the Regression method, obtaining measurements of the angle-of-attack solely through estimation causes problems in the estimation of the aerodynamic lift coefficients. Flight tests were performed and the data was analyzed. Similar issues as experienced with estimation done on the non-linear aircraft simulation, was found. Recommendations with regards to how to conduct future flight tests for system identification is proposed and possible sources of errors are highlighted. / AFRIKAANSE OPSOMMING: In hierdie tesis word die strategie vir die uitvoering van Stelsel Identifikasie op 'n vliegtuig aangebied. Die uiteindelike doel van hierdie document is om die stappe wat nodig is vir 'n suksesvolle vliegtuig parameter beraming, binne 'n Fout Tolerante Beheer Raamwerk, uit eente sit. 'n Kort afleiding van die klassieke 6 graad-van-vryheid vliegtuig model word eerstens aangebied. Die afleiding gee insig in die vliegtuig dinamika wat gebruik moet word om die vliegtuig parameters te beraam, en bied 'n basis vir die metodes wat in hierdie tesis verskyn. Verskillende tegnieke van Stelsel Identifikasie is geëvalueer, wat lei tot gebruik van die regressie-metode. Hierdie metode is gekies as gevolg van sy eenvoudigheid en omdat dit nie soveel berekening tyd as die ander metodes vereis nie. Regressie metodes, insluitend 'n rekursiewe algoritme, word dan toegepas op vliegtuig parameter beraming en praktiese orwegings soos identifiseerbaarheid en korrupte metings word uitgelig. Die bepaling van onbekende afmetings wat benodig is, word vir Stelsel Identifisering van die vliegtuig parameters bespreek. Metodes om die invalshoek en hoekige versnellings te meet en beraam, word aangebied. Die ontwerp en kalibrasie van 'n invalshoek sensor vir invalshoek metings, sowel as 'n nuwe metode wat gebruik maak van verspreide sensore om die hoekversnellings te bepaal, word ook aangebied. Die tegnieke wat in hierdie tesis aangebied is, word dan op 'n nie-lineêre vliegtuig model getoets. Deur simulasie is dit getoon dat die metodes vir die gegewe sensor opstelling nie voldoende akkurate parameters beraam nie. Dit is ook bewys dat met die gebruik van die Regressie metode, die vekryging van metings van die invalshoek slegs deur skatting, probleme in die beraming van die aerodinamiese lug koëffisiente veroorsaak. Die tegnieke wat in hierdie tesis verskyn, word dan op werklike vlug data toegepas.Vlugtoetse is uitgevoer en die data is ontleed. Aanbeveling met betrekking tot hoe om toekomstige vlug toetse vir Stelsel Identifikasiete word voorgestel, en moontlike bronne van foute word uitgelig.

Several configurations of Unmanned Aerial Vehicles (UAVs) were proposed to support different applications. One of them is the tailsitter, a fixed-wing aircraft that takes off and lands on its own tail, with the high endurance advantage from fixed-wing aircraft and, as helicopters and multicopters, not requiring a runway during takeoff and landing. However, a tailsitter has a complex operation with multiple flight stages, each one with its own particularities and requirements, which emphasises the necessity of a reliable autopilot for its use as a UAV. The literature already introduces tailsitter UAVs with complex mechanisms or with multiple counter-rotating propellers, but not one with only one propeller and without auxiliary structures to assist in the takeoff and landing. This thesis presents a tailsitter UAV, named AVALON (Autonomous VerticAL takeOff and laNding), and its autopilot, composed of 3 main units: Sensor Unit, Navigation Unit and Control Unit. In order to choose the most appropriate techniques for the autopilot, different solutions are evaluated. For Sensor Unit, Extended Kalman Filter and Unscented Kalman Filter estimate spatial information from multiple sensors data. Lookahead, Pure Pursuit and Line-of-Sight, Nonlinear Guidance Law and Vector Field path-following algorithms are extended to incorporate altitude information for Navigation Unit. In addition, a structure based on classical methods with decoupled Proportional-Integral-Derivative controllers is compared to a new control structure based on dynamic inversion. Together, all these techniques show the efficacy of AVALONs autopilot. Therefore, AVALON results in a small electric tailsitter UAV with a simple design, with only one propeller and without auxiliary structures to assist in the takeoff and landing, capable of executing all flight stages. / Diversas configurações de Veículos Aéreos Não Tripulados (VANTs) foram propostas para serem utilizadas em diferentes aplicações. Uma delas é o tailsitter, uma aeronave de asa fixa capaz de decolar e pousar sobre a própria cauda. Esse tipo de aeronave apresenta a vantagem de aeronaves de asa fixa de voar sobre grandes áreas com pouco tempo e bateria e, como helicópteros e multicópteros, não necessita de pista para decolar e pousar. Porém, um tailsitter possui uma operação complexa, com múltiplos estágios de voo, cada um com suas peculiaridades e requisitos, o que enfatiza a necessidade de um piloto automático confiável para seu uso como um VANT. A literatura já introduz VANTs tailsitters com mecanismos complexos ou múltiplos motores contra-rotativos, mas não com apenas um motor e sem estruturas para auxiliar no pouso e na decolagem. Essa tese apresenta um VANT tailsitter, chamado AVALON (Autonomous VerticAL takeOff and laNding), e seu piloto automático, composto por 3 unidades principais: Unidade Sensorial, Unidade de Navegação e Unidade de Controle. Diferentes soluções são avaliadas para a escolha das técnicas mais apropriadas para o piloto automático. Para a Unidade Sensorial, Extended Kalman Filter e Unscented Kalman Filter estimam a informação espacial de múltiplos dados de diversos sensores. Os algoritmos de seguimento de trajetória Lookahead, Pure Pursuit and Line-of-Sight, Nonlinear Guidance Law e Vector Field são estendidos para considerar a informação da altitude para a Unidade de Navegação. Além do mais, uma estrutura baseada em métodos clássicos com controladores Proporcional- Integral-Derivativo desacoplados é comparada a uma nova estrutura de controle baseada em dinâmica inversa. Juntas, todas essas técnicas demonstram a eficácia do piloto automático do AVALON. Portanto, AVALON resulta em um VANT tailsitter pequeno e elétrico, com um design simples, apenas um motor e sem estruturas para auxiliar o pouso e a decolagem, capaz de executar todos os estágios de voo.

Quad-rotor micro-UAVs have become an important tool in the field of indoor UAV research. Indoor flight poses problems not experienced in outdoor applications. The ability to be location- and movement-aware is paramount because of the close proximity of obstacles (walls, doorways, desks). The Helio-copter, an indoor quad-rotor platform that utilizes a compact FPGA board called Helios has been developed in the Robotic Vision Lab at Brigham Young University. Helios allows researchers to perform on-board vision processing and feature tracking without the aid of a ground station or wireless transmission. Using this on-board feature tracking system a drift stabilization control system has been developed that allows indoor flight of the Helio-copter without tethers. The Helio-copter uses an IMU to maintain level attitude while processing camera images on the FPGA. The FPGA then computes translation, scale, and rotation deviations from camera image feedback. An on-board system has been developed to control yaw, altitude and drift based solely on the vision sensors. Preliminary testing shows the Helio-copter capable of maintaining level, stable flight within a 6 foot by 6 foot area for over 40 seconds without human intervention using basic PID loop structures with minor tuning. The integration of the vision system into the control structures is explained.

The focus of this thesis is on Actual Entities, a concept created by the philosopher Alfred North Whitehead, and how the concept can be applied to Unmanned Aerial Vehicles as a behavioral control method. Actual Entities are vector based, atomic units that use a method called prehension to observe their environment and react with various actions. When combining multiple Actual Entities a Colony of Prehending Entities is created; when observing their prehensions an intelligent behavior emerges. By applying the characteristics of Actual Entities to Unmanned Aerial Vehicles, specifically in a situation where they are searching for targets, this emergent, intelligent behavior can be seen as they search a designated area and locate specified targets. They will alter their movements based on the prehensions of the environment, surrounding Unmanned Aerial Vehicles, and targets.