Integrated architecture for vision-based indoor localization and mapping of a quadrotor micro-air vehicle

Atualmente os sistemas de pilotagem autónoma de quadricópteros estão a ser desenvolvidos de forma a efetuarem navegação em espaços exteriores, onde o sinal de GPS pode ser utilizado para definir waypoints de navegação, modos de position e altitude hold, returning home, entre outros. Contudo, o problema de navegação autónoma em espaços fechados sem que se utilize um sistema de posicionamento global dentro de uma sala, subsiste como um problema desafiante e sem solução fechada. Grande parte das soluções são baseadas em sensores dispendiosos, como o LIDAR ou como sistemas de posicionamento externos (p.ex. Vicon, Optitrack). Algumas destas soluções reservam a capacidade de processamento de dados dos sensores e dos algoritmos mais exigentes para sistemas de computação exteriores ao veículo, o que também retira a componente de autonomia total que se pretende num veículo com estas características. O objetivo desta tese pretende, assim, a preparação de um sistema aéreo não-tripulado de pequeno porte, nomeadamente um quadricóptero, que integre diferentes módulos que lhe permitam simultânea localização e mapeamento em espaços interiores onde o sinal GPS ´e negado, utilizando, para tal, uma câmara RGB-D, em conjunto com outros sensores internos e externos do quadricóptero, integrados num sistema que processa o posicionamento baseado em visão e com o qual se pretende que efectue, num futuro próximo, planeamento de movimento para navegação. O resultado deste trabalho foi uma arquitetura integrada para análise de módulos de localização, mapeamento e navegação, baseada em hardware aberto e barato e frameworks state-of-the-art disponíveis em código aberto. Foi também possível testar parcialmente alguns módulos de localização, sob certas condições de ensaio e certos parâmetros dos algoritmos. A capacidade de mapeamento da framework também foi testada e aprovada. A framework obtida encontra-se pronta para navegação, necessitando apenas de alguns ajustes e testes.

Emergency care systems demonstration projects. Volume 2: the emergency care system. Final report.

National Highway Safety Bureau, Washington, D.C.

Approximate, Average, Dynamic Models of Uncontrolled Rectifiers for Aircraft Applications

To carry out stability and voltage regulation studies on more electric aircraft systems in which there is a preponderance of multi-pulse, rectifier-fed motor-drive equipment, average dynamic models of the rectifier converters are required. Existing methods are difficult to apply to anything other than single converters with a low pulse number. Therefore an efficient, compact method for deriving the approximate, linear, average model of 6- and 12-pulse rectifiers, based on the assumption of a small duration of the overlap angle is presented. The models are validated against detailed simulations and laboratory prototypes.

On precise three-dimensional environment modeling via UAV-based photogrammetric systems

Abstract : Images acquired from unmanned aerial vehicles (UAVs) can provide data with unprecedented spatial and temporal resolution for three-dimensional (3D) modeling. Solutions developed for this purpose are mainly operating based on photogrammetry concepts, namely UAV-Photogrammetry Systems (UAV-PS). Such systems are used in applications where both geospatial and visual information of the environment is required. These applications include, but are not limited to, natural resource management such as precision agriculture, military and police-related services such as traffic-law enforcement, precision engineering such as infrastructure inspection, and health services such as epidemic emergency management. UAV-photogrammetry systems can be differentiated based on their spatial characteristics in terms of accuracy and resolution. That is some applications, such as precision engineering, require high-resolution and high-accuracy information of the environment (e.g. 3D modeling with less than one centimeter accuracy and resolution). In other applications, lower levels of accuracy might be sufficient, (e.g. wildlife management needing few decimeters of resolution). However, even in those applications, the specific characteristics of UAV-PSs should be well considered in the steps of both system development and application in order to yield satisfying results. In this regard, this thesis presents a comprehensive review of the applications of unmanned aerial imagery, where the objective was to determine the challenges that remote-sensing applications of UAV systems currently face. This review also allowed recognizing the specific characteristics and requirements of UAV-PSs, which are mostly ignored or not thoroughly assessed in recent studies. Accordingly, the focus of the first part of this thesis is on exploring the methodological and experimental aspects of implementing a UAV-PS. The developed system was extensively evaluated for precise modeling of an open-pit gravel mine and performing volumetric-change measurements. This application was selected for two main reasons. Firstly, this case study provided a challenging environment for 3D modeling, in terms of scale changes, terrain relief variations as well as structure and texture diversities. Secondly, open-pit-mine monitoring demands high levels of accuracy, which justifies our efforts to improve the developed UAV-PS to its maximum capacities. The hardware of the system consisted of an electric-powered helicopter, a high-resolution digital camera, and an inertial navigation system. The software of the system included the in-house programs specifically designed for camera calibration, platform calibration, system integration, onboard data acquisition, flight planning and ground control point (GCP) detection. The detailed features of the system are discussed in the thesis, and solutions are proposed in order to enhance the system and its photogrammetric outputs. The accuracy of the results was evaluated under various mapping conditions, including direct georeferencing and indirect georeferencing with different numbers, distributions and types of ground control points. Additionally, the effects of imaging configuration and network stability on modeling accuracy were assessed. The second part of this thesis concentrates on improving the techniques of sparse and dense reconstruction. The proposed solutions are alternatives to traditional aerial photogrammetry techniques, properly adapted to specific characteristics of unmanned, low-altitude imagery. Firstly, a method was developed for robust sparse matching and epipolar-geometry estimation. The main achievement of this method was its capacity to handle a very high percentage of outliers (errors among corresponding points) with remarkable computational efficiency (compared to the state-of-the-art techniques). Secondly, a block bundle adjustment (BBA) strategy was proposed based on the integration of intrinsic camera calibration parameters as pseudo-observations to Gauss-Helmert model. The principal advantage of this strategy was controlling the adverse effect of unstable imaging networks and noisy image observations on the accuracy of self-calibration. The sparse implementation of this strategy was also performed, which allowed its application to data sets containing a lot of tie points. Finally, the concepts of intrinsic curves were revisited for dense stereo matching. The proposed technique could achieve a high level of accuracy and efficiency by searching only through a small fraction of the whole disparity search space as well as internally handling occlusions and matching ambiguities. These photogrammetric solutions were extensively tested using synthetic data, close-range images and the images acquired from the gravel-pit mine. Achieving absolute 3D mapping accuracy of 11±7 mm illustrated the success of this system for high-precision modeling of the environment.

Drones y el orden legal internacional. Tecnología, estrategia y largas cadenas de acción

The main thesis of this article is that the increasing recourse to the use of unmanned aerial systems in asymmetric warfare and the beginning routinization of U.S. drone operations represent part of an evolutionary change in the spatial ordering of global politics -- Using a heuristic framework based on actor-network theory, it is argued that practices of panoptic observation and selective airstrikes, being in need of legal justification, contribute to a reterritorialization of asymmetric conflicts -- Under a new normative spatial regime, a legal condition of state immaturity is constructed, which establishes a zone of conditional sovereignty subject to transnational aerial policing -- At the same time, this process is neither a deterministic result of the new technology nor a deliberate effect of policies to which drones are merely neutral instruments -- Rather, military technology and political decisions both form part of a long chain of action which has evolved under the specific circumstances of recent military interventions

Radar Based Collision detection developments on USV ROAZ II

This work presents the integration of obstacle detection and analysis capabilities in a coherent and advanced C&C framework allowing mixed-mode control in unmanned surface systems. The collision avoidance work has been successfully integrated in an operational autonomous surface vehicle and demonstrated in real operational conditions. We present the collision avoidance system, the ROAZ autonomous surface vehicle and the results obtained at sea tests. Limitations of current COTS radar systems are also discussed and further research directions are proposed towards the development and integration of advanced collision avoidance systems taking in account the different requirements in unmanned surface vehicles.

Geospatial assessment of pest-induced forest damage through the use of UAV-bases NIR imaging and Gi-technology

Dissertation submitted in partial fulfillment of the requirements for the Degree of Master of Science in Geospatial Technologies.

Prácticas docentes con simuladores de vuelo

Este trabajo presenta las prácticas de laboratorio de la asignatura de Tecnología Aaeroespacial, perteneciente a la titulación de Ingeniería Técnica Aeronáutica (especialidad en Aeronavegación) y que se imparte en la Escuela Politécnica Superior de Castelldefels (EPSC) de laUniversidad Politécnica de Catalunya (UPC). Dichas prácticas se desarrollan en grupos de dos estudiantes alrededor de un conocido programa de simulación de vuelo y permiten al alumno ver y profundizar en los diferentes aspectos tratados en las clases teóricas de una manera próxima a la realidad y muy amigable.El alumno debe afrontarse a situaciones que, a lo largo de las diferentes sesiones de laboratorio, aumentan progresivamente en complejidad y conocimientos previos necesarios para resolverlas. Con esto, se llega a la práctica final donde cada pareja de estudiantes realiza un vuelo completosimulado de principio a fin que ha ido preparando y experimentando por partes durante el curso.Además, este vuelo se realiza en un entorno de simulación de tráfico aéreo en tiempo real con control del tráfico aéreo virtual (formado por estudiantes voluntarios de cursos superiores) que da aun más realismo a la simulación.Después de seis cursos consecutivos realizando esta experiencia, este trabajo concluye que este tipo de prácticas motivan significativamente al alumno a profundizar en los aspectos de la asignatura y potencian el trabajo cooperativo y el aprendizaje basado en proyectos.

Precision Agriculture without borders: Practical issues and improvements in farmland coverage with aerial vehicles.

This work presents a solution for the aerial coverage of a field by using a fleet of aerial vehicles. The use of Unmanned Aerial Vehicles allows to obtain high resolution mosaics to be used in Precision Agriculture techniques. This report is focus on providing a solution for the full simultaneous coverage problem taking into account restrictions as the required spatial resolution and overlap while maintaining similar light conditions and safety operation of the drones. Results obtained from real field tests are finally reported

Análisis de la influencia del borde de salida abierto en perfiles aerodinámicos a bajos números de Reynolds

El objetivo del presente trabajo es analizar la influencia que tiene sobre el comportamiento aerodinámico del perfil el hecho de que este presente un borde de salida más grueso que el perfil original del que se partía. Este estudio se ha centrado fundamentalmente en la influencia sobre su sustentación aerodinámica, resistencia aerodinámica y, especialmente, sobre la eficiencia aerodinámica del perfil, es decir sobre la relación entre la sustentación y la resistencia aerodinámica. También se ha analizado su influencia en otros aspectos aerodinámicos de los perfiles, como la entrada en pérdida, el ángulo de ataque de sustentación máxima, el ángulo de ataque de eficiencia máxima, el coeficiente de momento aerodinámico y la posición del centro aerodinámico. Estas imperfecciones en el borde de salida pueden aparecer en algunos procesos de fabricación de determinados elementos aerodinámicos, como alas de aviones no tripulados o palas de aeroturbina. Este fenómeno no ha sido analizado en profundidad en la literatura científica, aunque si que se ha analizado por varios autores la influencia sobre el perfil con el borde de salida truncado, o perfiles con la parte final regruesada, utilizados en otras aplicaciones. Para la realización de este estudio se han analizado perfiles de distinto tipo, laminares y no laminares, perfiles simétricos y con curvatura, así como perfiles con distinto espesor, a fin de comparar el grado de influencia del fenómeno estudiado sobre cada tipo de perfil para comparar su grado de sensibilidad a dicha anomalía geométrica. El estudio se ha realizado experimentalmente utilizando una cámara de ensayos diseñada específicamente a tal efecto, así como una balanza electrónica para medir las fuerzas y los momentos sobre el perfil, y un escáner de presiones para medir la distribución de presiones en determinados casos. También se ha abordado el estudio del comportamiento de perfiles con borde de salida más grueso que el nominal pero redondeado en vez de romo, con el objeto de analizar la eficacia de redondear el borde de salida, que es uno de los métodos que se puede utilizar para mitigar este efecto. Por otro lado, como el comportamiento de los perfiles aerodinámicos tiene una fuerte dependencia del número de Reynolds, el estudio se ha centrado en el análisis del comportamiento a bajos números de Reynolds debido a su uso reciente en una amplia gama de aplicaciones, desde vehículos aéreos no tripulados (UAV) hasta palas de aeroturbinas de baja potencia, e incluso debido a su uso potencial en aeronaves diseñadas para volar en atmósferas de baja densidad como la que existe en Marte. El interés de este estudio está orientado al establecimiento de criterios para cuantificar la influencia que tiene el hecho de que el borde de salida sea más grueso que el nominal en la degradación de su eficiencia aerodinámica máxima, con el objeto de poder establecer los límites de aceptación o rechazo de estas piezas una vez fabricadas, según el tipo de perfil aerodinámico utilizado. Del resultado del análisis de los casos estudiados se puede concluir que según aumenta el espesor del borde de salida, dentro del intervalo de estudio, la sustentación aerodinámica aumenta, así como la sustentación máxima, pero aumenta en mayor proporción la resistencia aerodinámica, por lo que se produce una reducción de la eficiencia aerodinámica, en particular de su valor máximo. Por otro lado, el hecho de redondear el borde de salida del perfil ayuda ligeramente a reducir este efecto. ABSTRACT The aim of this thesis is to analyze the effects of airfoil trailing edges thickness when this is thicker than the airfoil nominal. Several factors may lead to an airfoil trailing edge being thicker than the nominal airfoil, and this may affect various aerodynamic parameters. This study has focus on its influence on the airfoil’s aerodynamic lift, drag and, particularly on the aerodynamic efficiency of the airfoil, that is, the relationship between the aerodynamic lift and drag. It has also been studied how this fact may alter some other aerodynamic aspects of airfoils, such as stall, angle of attack of maximum lift, angle of maximum efficiency, aerodynamic moment coefficient and aerodynamic center position. These imperfections in the trailing edge may appear in some manufacturing processes of certain aerodynamic elements, such as unmanned aircraft wings or wind turbine blades. This phenomenon has not been deeply analyzed in the literature, although several authors have discussed its influence on airfoil with truncated trailing edge, or airfoils with thickened end, used in other applications. Various types of airfoils have been analyzed, laminar and non-laminar, symmetric and curved airfoils, and airfoils with different thickness, in order to compare the degree of influence of the phenomenon studied on each airfoil type and thus, to estimate the degree of sensitivity to the anomaly geometry. The study was carried out experimentally using a test chamber designed specifically for this purpose, as well as an electronic balance to measure the forces and moments on the airfoil, and a pressure scanner to measure distribution of pressures in certain cases. It has also been investigated the behavior of airfoils with trailing edge thicker than the nominal, but rounded instead of blunt, in order to analyze the effectiveness of the trailing edge rounding, which is one of the methods that can be used to mitigate this phenomenon. Moreover, as the behavior of the airfoil is highly dependent on the Reynolds number, the study has been focused on the analysis of the behavior at low Reynolds numbers due to recent use of low Reynolds numbers airfoils in a wide range of applications, from unmanned aerial vehicles (UAV) to low power wind turbine blades, or even due to their potential use in aircraft designed to fly in low density atmospheres as the one existing in Mars. The main purpose of this research is to establish a set of criteria for quantifying the influence that a thicker-than–nominal-trailing edge has in the degradation of maximum aerodynamic efficiency, aiming at establishing the acceptance limits for these pieces when they are manufactured, according to the type of airfoil used. Based on the results obtained from the analysis of the cases under study it can be concluded that increasing the thickness of the trailing edge, within the range of study, increases aerodynamic lift, as well as maximum lift, but the aerodynamic drag increases in a higher proportion, and consequently there is a reduction of aerodynamic efficiency, particularly, of its maximum value. On the other hand, rounding the trailing edge of the airfoil slightly helps to reduce this effect.

Análisis de la influencia de imperfecciones en el borde de ataque en perfiles aerodinámicos a bajos números de Reynolds

En esta tesis se ha analizado la influencia que tienen ciertas imperfecciones en el borde de ataque de un perfil aerodinámico sobre el comportamiento aerodinámico general del mismo, centrándose fundamentalmente en la influencia sobre el coeficiente de sustentación máxima, coeficiente de resistencia y sobre la eficiencia aerodinámica del perfil, es decir sobre la relación entre la sustentación y la resistencia aerodinámicas. También se ha analizado su influencia en otros aspectos, como la entrada en pérdida, ángulo de ataque de sustentación máxima, ángulo de ataque de eficiencia máxima, coeficiente de momento aerodinámico y posición del centro aerodinámico. Estos defectos de forma en el borde de ataque pueden aparecer en algunos procesos de fabricación de determinados elementos aerodinámicos, como pueden ser las alas de pequeños aviones no tripulados o las palas de aeroturbina. Los perfiles se ha estudiado a bajos números de Reynolds debido a su uso reciente en una amplia gama de aplicaciones, desde vehículos aéreos no tripulados (UAV) hasta palas de aeroturbina de baja potencia, e incluso debido a su potencial utilización en aeronaves diseñadas para volar en atmósferas de baja densidad. El objeto de estudio de esta tesis no ha sido analizado en profundidad en la literatura científica, aunque sí que se ha estudiado por varios autores el comportamiento de perfiles a bajos números de Reynolds, con ciertas protuberancias sobre su superficie o también con formación de hielo en el borde de ataque. Para la realización de este estudio se han analizado perfiles de distinto tipo, perfiles simétricos y con curvatura, perfiles laminares, y todos ellos con igual o distinto espesor, con el objeto de obtener y comparar la influencia del fenómeno estudiado sobre cada tipo de perfil y así analizar su grado de sensibilidad a estas imperfecciones en la geometría del borde de ataque. Este trabajo ha sido realizado experimentalmente utilizando una túnel aerodinámico diseñado específicamente a tal efecto, así como una balanza electrónica para medir las fuerzas y los momentos sobre el perfil, y un escáner de presiones para medir la distribución de presiones sobre la superficie de los perfiles en determinados casos de interés. La finalidad de este estudio está orientada al establecimiento de criterios para cuantificar la influencia en la aerodinámica del perfil que tiene el hecho de que el borde de ataque presente una discontinuidad geométrica, con el objeto de poder establecer los límites de aceptación o rechazo de estas piezas en el momento de ser fabricadas. Del análisis de los casos estudiados se puede concluir que según aumenta el tamaño de la imperfección del borde de ataque, la sustentación aerodinámica máxima en general disminuye, al igual que la eficiencia aerodinámica máxima, pues la resistencia aerodinámica aumenta. Sin embargo, en algunos casos, para pequeños defectos se produce un efecto contrario. La sustentación máxima aumenta apreciablemente sin apenas pérdida de eficiencia aerodinámica máxima. ABSTRACT The aim of this thesis is to analyze the effects of leading edge imperfections on the aerodynamic characteristics of airfoils at low Reynolds numbers. The leading edge imperfection here considered being a slight displacement of half airfoil with respect to the other. This study has focus on its influence on the airfoil’s aerodynamic lift, drag and on the aerodynamic efficiency of the airfoil, that is, the relationship between the aerodynamic lift and drag. It has also been studied how this fact may alter some other aerodynamic aspects of airfoils, such as stall, angle of attack of maximum lift, angle of maximum efficiency, aerodynamic moment coefficient and aerodynamic center position. These imperfections in the leading edge may appear in some manufacturing processes of certain aerodynamic elements, such as unmanned aircraft wings or wind turbine blades. The study has focused on the analysis of the behavior at low Reynolds numbers due to recent use of low Reynolds numbers airfoils in a wide range of applications, from unmanned aerial vehicles (UAV) to low power wind turbine blades, or even due to their potential use in aircraft designed to fly in low density atmospheres as the one existing in Mars. This phenomenon has not been deeply analyzed in the literature, although several authors have discussed on airfoils at low Reynolds number, with leading edge protuberances or airfoils with ice accretions. Various types of airfoils have been analyzed, laminar and non-laminar, symmetric and curved airfoils, and airfoils with different thickness, in order to compare the degree of influence of the phenomenon studied on each airfoil type and thus, to estimate the degree of sensitivity to the anomaly geometry. The study was carried out experimentally using a test chamber designed specifically for this purpose, as well as an electronic balance to measure the forces and moments on the airfoil, and a pressure scanner to measure distribution of pressures in certain cases. The main purpose of this research is to establish a criteria for quantifying the influence that a slight displacement of half aerofoil with respect to the other has in the degradation of aerodynamics characteristics, aiming at establishing the acceptance limits for these pieces when they are manufactured, according to the type of airfoil used. Based on the results obtained from the analysis of the cases under study it can be concluded that displacements, within the range of study, decreases maximum aerodynamic lift, but the aerodynamic drag increases, and consequently there is a reduction of aerodynamic efficiency. However, in some cases, for small defects opposite effect occurs. The maximum lift increases significantly with little loss of maximum aerodynamic efficiency.

Real-time determination of airspace wind speed field based on FDR = Determinación en tiempo real del campo de velocidad del viento basado en registradores de datos de vuelo

El estudio del comportamiento de la atmósfera ha resultado de especial importancia tanto en el programa SESAR como en NextGen, en los que la gestión actual del tránsito aéreo (ATM) está experimentando una profunda transformación hacia nuevos paradigmas tanto en Europa como en los EE.UU., respectivamente, para el guiado y seguimiento de las aeronaves en la realización de rutas más eficientes y con mayor precisión. La incertidumbre es una característica fundamental de los fenómenos meteorológicos que se transfiere a la separación de las aeronaves, las trayectorias de vuelo libres de conflictos y a la planificación de vuelos. En este sentido, el viento es un factor clave en cuanto a la predicción de la futura posición de la aeronave, por lo que tener un conocimiento más profundo y preciso de campo de viento reducirá las incertidumbres del ATC. El objetivo de esta tesis es el desarrollo de una nueva técnica operativa y útil destinada a proporcionar de forma adecuada y directa el campo de viento atmosférico en tiempo real, basada en datos de a bordo de la aeronave, con el fin de mejorar la predicción de las trayectorias de las aeronaves. Para lograr este objetivo se ha realizado el siguiente trabajo. Se han descrito y analizado los diferentes sistemas de la aeronave que proporcionan las variables necesarias para obtener la velocidad del viento, así como de las capacidades que permiten la presentación de esta información para sus aplicaciones en la gestión del tráfico aéreo. Se ha explorado el uso de aeronaves como los sensores de viento en un área terminal para la estimación del viento en tiempo real con el fin de mejorar la predicción de las trayectorias de aeronaves. Se han desarrollado métodos computacionalmente eficientes para estimar las componentes horizontales de la velocidad del viento a partir de las velocidades de las aeronaves (VGS, VCAS/VTAS), la presión y datos de temperatura. Estos datos de viento se han utilizado para estimar el campo de viento en tiempo real utilizando un sistema de procesamiento de datos a través de un método de mínima varianza. Por último, se ha evaluado la exactitud de este procedimiento para que esta información sea útil para el control del tráfico aéreo. La información inicial proviene de una muestra de datos de Registradores de Datos de Vuelo (FDR) de aviones que aterrizaron en el aeropuerto Madrid-Barajas. Se dispuso de datos de ciertas aeronaves durante un periodo de más de tres meses que se emplearon para calcular el vector viento en cada punto del espacio aéreo. Se utilizó un modelo matemático basado en diferentes métodos de interpolación para obtener los vectores de viento en áreas sin datos disponibles. Se han utilizado tres escenarios concretos para validar dos métodos de interpolación: uno de dos dimensiones que trabaja con ambas componentes horizontales de forma independiente, y otro basado en el uso de una variable compleja que relaciona ambas componentes. Esos métodos se han probado en diferentes escenarios con resultados dispares. Esta metodología se ha aplicado en un prototipo de herramienta en MATLAB © para analizar automáticamente los datos de FDR y determinar el campo vectorial del viento que encuentra la aeronave al volar en el espacio aéreo en estudio. Finalmente se han obtenido las condiciones requeridas y la precisión de los resultados para este modelo. El método desarrollado podría utilizar los datos de los aviones comerciales como inputs utilizando los datos actualmente disponibles y la capacidad computacional, para proporcionárselos a los sistemas ATM donde se podría ejecutar el método propuesto. Estas velocidades del viento calculadas, o bien la velocidad respecto al suelo y la velocidad verdadera, se podrían difundir, por ejemplo, a través del sistema de direccionamiento e informe para comunicaciones de aeronaves (ACARS), mensajes de ADS-B o Modo S. Esta nueva fuente ayudaría a actualizar la información del viento suministrada en los productos aeronáuticos meteorológicos (PAM), informes meteorológicos de aeródromos (AIRMET), e información meteorológica significativa (SIGMET). ABSTRACT The study of the atmosphere behaviour is been of particular importance both in SESAR and NextGen programs, where the current air traffic management (ATM) system is undergoing a profound transformation to the new paradigms both in Europe and the USA, respectively, to guide and track aircraft more precisely on more efficient routes. Uncertainty is a fundamental characteristic of weather phenomena which is transferred to separation assurance, flight path de-confliction and flight planning applications. In this respect, the wind is a key factor regarding the prediction of the future position of the aircraft, so that having a deeper and accurate knowledge of wind field will reduce ATC uncertainties. The purpose of this thesis is to develop a new and operationally useful technique intended to provide adequate and direct real-time atmospheric winds fields based on on-board aircraft data, in order to improve aircraft trajectory prediction. In order to achieve this objective the following work has been accomplished. The different sources in the aircraft systems that provide the variables needed to derivate the wind velocity have been described and analysed, as well as the capabilities which allow presenting this information for air traffic management applications. The use of aircraft as wind sensors in a terminal area for real-time wind estimation in order to improve aircraft trajectory prediction has been explored. Computationally efficient methods have been developed to estimate horizontal wind components from aircraft velocities (VGS, VCAS/VTAS), pressure, and temperature data. These wind data were utilized to estimate a real-time wind field using a data processing approach through a minimum variance method. Finally, the accuracy of this procedure has been evaluated for this information to be useful to air traffic control. The initial information comes from a Flight Data Recorder (FDR) sample of aircraft landing in Madrid-Barajas Airport. Data available for more than three months were exploited in order to derive the wind vector field in each point of the airspace. Mathematical model based on different interpolation methods were used in order to obtain wind vectors in void areas. Three particular scenarios were employed to test two interpolation methods: a two-dimensional one that works with both horizontal components in an independent way, and also a complex variable formulation that links both components. Those methods were tested using various scenarios with dissimilar results. This methodology has been implemented in a prototype tool in MATLAB © in order to automatically analyse FDR and determine the wind vector field that aircraft encounter when flying in the studied airspace. Required conditions and accuracy of the results were derived for this model. The method developed could be fed by commercial aircraft utilizing their currently available data sources and computational capabilities, and providing them to ATM system where the proposed method could be run. Computed wind velocities, or ground and true airspeeds, would then be broadcasted, for example, via the Aircraft Communication Addressing and Reporting System (ACARS), ADS-B out messages, or Mode S. This new source would help updating the wind information furnished in meteorological aeronautical products (PAM), meteorological aerodrome reports (AIRMET), and significant meteorological information (SIGMET).

Two NextGen Air Safety Tools: An ADS-B Equipped UAV and a Wake Turbulence Estimator

Thesis (Master's)--University of Washington, 2016-06

New developments in UAV remote sensing for pest management and the implications for cotton

Efficient crop monitoring and pest damage assessments are key to protecting the Australian agricultural industry and ensuring its leading position internationally. An important element in pest detection is gathering reliable crop data frequently and integrating analysis tools for decision making. Unmanned aerial systems are emerging as a cost-effective solution to a number of precision agriculture challenges. An important advantage of this technology is it provides a non-invasive aerial sensor platform to accurately monitor broad acre crops. In this presentation, we will give an overview on how unmanned aerial systems and machine learning can be combined to address crop protection challenges. A recent 2015 study on insect damage in sorghum will illustrate the effectiveness of this methodology. A UAV platform equipped with a high-resolution camera was deployed to autonomously perform a flight pattern over the target area. We describe the image processing pipeline implemented to create a georeferenced orthoimage and visualize the spatial distribution of the damage. An image analysis tool has been developed to minimize human input requirements. The computer program is based on a machine learning algorithm that automatically creates a meaningful partition of the image into clusters. Results show the algorithm delivers decision boundaries that accurately classify the field into crop health levels. The methodology presented in this paper represents a venue for further research towards automated crop protection assessments in the cotton industry, with applications in detecting, quantifying and monitoring the presence of mealybugs, mites and aphid pests.

Networked embedded systems for active flow control in aircraft

Aerodynamic drag is known to be one of the factors contributing more to increased aircraft fuel consumption. The primary source of skin friction drag during flight is the boundary layer separation. This is the layer of air moving smoothly in the immediate vicinity of the aircraft. In this paper we discuss a cyber-physical system approach able of performing an efficient suppression of the turbulent flow by using a dense sensing deployment to detect the low pressure region and a similarly dense deployment of actuators to manage the turbulent flow. With this concept, only the actuators in the vicinity of a separation layer are activated, minimizing power consumption and also the induced drag.