A General Purpose Configurable Controller for Indoors and Outdoors GPS-Denied Navigation for Multirotor Unmanned Aerial Vehicles

This research on odometry based GPS-denied navigation on multirotor Unmanned Aerial Vehicles is focused among the interactions between the odometry sensors and the navigation controller. More precisely, we present a controller architecture that allows to specify a speed specified flight envelope where the quality of the odometry measurements is guaranteed. The controller utilizes a simple point mass kinematic model, described by a set of configurable parameters, to generate a complying speed plan. For experimental testing, we have used down-facing camera optical-flow as odometry measurement. This work is a continuation of prior research to outdoors environments using an AR Drone 2.0 vehicle, as it provides reliable optical flow on a wide range of flying conditions and floor textures. Our experiments show that the architecture is realiable for outdoors flight on altitudes lower than 9 m. A prior version of our code was utilized to compete in the International Micro Air Vehicle Conference and Flight Competition IMAV 2012. The code will be released as an open-source ROS stack hosted on GitHub.

UAS See-and-Avoid Strategy using a Fuzzy Logic Controller Optimized by Cross-Entropy in Scaling Factors and Membership Functions.

This work aims to develop a novel Cross-Entropy (CE) optimization-based fuzzy controller for Unmanned Aerial Monocular Vision-IMU System (UAMVIS) to solve the seeand-avoid problem using its accurate autonomous localization information. The function of this fuzzy controller is regulating the heading of this system to avoid the obstacle, e.g. wall. In the Matlab Simulink-based training stages, the Scaling Factor (SF) is adjusted according to the specified task firstly, and then the Membership Function (MF) is tuned based on the optimized Scaling Factor to further improve the collison avoidance performance. After obtained the optimal SF and MF, 64% of rules has been reduced (from 125 rules to 45 rules), and a large number of real flight tests with a quadcopter have been done. The experimental results show that this approach precisely navigates the system to avoid the obstacle. To our best knowledge, this is the first work to present the optimized fuzzy controller for UAMVIS using Cross-Entropy method in Scaling Factors and Membership Functions optimization.

A General Purpose Configurable Navigation Controller for Micro Aerial Multirotor Vehicles

In this paper, we consider the problem of autonomous navigation of multirotor platforms in GPS-denied environments. The focus of this work is on safe navigation based on unperfect odometry measurements, such as on-board optical flow measurements. The multirotor platform is modeled as a flying object with specific kinematic constraints that must be taken into account in order to obtain successful results. A navigation controller is proposed featuring a set of configurable parameters that allow, for instance, to have a configuration setup for fast trajectory following, and another to soften the control laws and make the vehicle navigation more precise and slow whenever necessary. The proposed controller has been successfully implemented in two different multirotor platforms with similar sensoring capabilities showing the openness and tolerance of the approach. This research is focused around the Computer Vision Group's objective of applying multirotor vehicles to civilian service applications. The presented work was implemented to compete in the International Micro Air Vehicle Conference and Flight Competition IMAV 2012, gaining two awards: the Special Award on "Best Automatic Performance - IMAV 2012" and the second overall prize in the participating category "Indoor Flight Dynamics - Rotary Wing MAV". Most of the code related to the present work is available as two open-source projects hosted in GitHub.

Optimization of the Integrated Guidance and Control for a Dual Aerodynamic Control Missile

Las futuras misiones para misiles aire-aire operando dentro de la atmósfera requieren la interceptación de blancos a mayores velocidades y más maniobrables, incluyendo los esperados vehículos aéreos de combate no tripulados. La intercepción tiene que lograrse desde cualquier ángulo de lanzamiento. Una de las principales discusiones en la tecnología de misiles en la actualidad es cómo satisfacer estos nuevos requisitos incrementando la capacidad de maniobra del misil y en paralelo, a través de mejoras en los métodos de guiado y control modernos. Esta Tesis aborda estos dos objetivos simultáneamente, al proponer un diseño integrando el guiado y el control de vuelo (autopiloto) y aplicarlo a misiles con control aerodinámico simultáneo en canard y cola. Un primer avance de los resultados obtenidos ha sido publicado recientemente en el Journal of Aerospace Engineering, en Abril de 2015, [Ibarrondo y Sanz-Aranguez, 2015]. El valor del diseño integrado obtenido es que permite al misil cumplir con los requisitos operacionales mencionados empleando únicamente control aerodinámico. El diseño propuesto se compara favorablemente con esquemas más tradicionales, consiguiendo menores distancias de paso al blanco y necesitando de menores esfuerzos de control incluso en presencia de ruidos. En esta Tesis se demostrará cómo la introducción del doble mando, donde tanto el canard como las aletas de cola son móviles, puede mejorar las actuaciones de un misil existente. Comparado con un misil con control en cola, el doble control requiere sólo introducir dos servos adicionales para accionar los canards también en guiñada y cabeceo. La sección de cola será responsable de controlar el misil en balanceo mediante deflexiones diferenciales de los controles. En el caso del doble mando, la complicación añadida es que los vórtices desprendidos de los canards se propagan corriente abajo y pueden incidir sobre las superficies de cola, alterando sus características de control. Como un primer aporte, se ha desarrollado un modelo analítico completo para la aerodinámica no lineal de un misil con doble control, incluyendo la caracterización de este efecto de acoplamiento aerodinámico. Hay dos modos de funcionamiento en picado y guiñada para un misil de doble mando: ”desviación” y ”opuesto”. En modo ”desviación”, los controles actúan en la misma dirección, generando un cambio inmediato en la sustentación y produciendo un movimiento de translación en el misil. La respuesta es rápida, pero en el modo ”desviación” los misiles con doble control pueden tener dificultades para alcanzar grandes ángulos de ataque y altas aceleraciones laterales. Cuando los controles actúan en direcciones opuestas, el misil rota y el ángulo de ataque del fuselaje se incrementa para generar mayores aceleraciones en estado estacionario, aunque el tiempo de respuesta es mayor. Con el modelo aerodinámico completo, es posible obtener una parametrización dependiente de los estados de la dinámica de corto periodo del misil. Debido al efecto de acoplamiento entre los controles, la respuesta en bucle abierto no depende linealmente de los controles. El autopiloto se optimiza para obtener la maniobra requerida por la ley de guiado sin exceder ninguno de los límites aerodinámicos o mecánicos del misil. Una segunda contribución de la tesis es el desarrollo de un autopiloto con múltiples entradas de control y que integra la aerodinámica no lineal, controlando los tres canales de picado, guiñada y cabeceo de forma simultánea. Las ganancias del autopiloto dependen de los estados del misil y se calculan a cada paso de integración mediante la resolución de una ecuación de Riccati de orden 21x21. Las ganancias obtenidas son sub-óptimas, debido a que una solución completa de la ecuación de Hamilton-Jacobi-Bellman no puede obtenerse de manera práctica, y se asumen ciertas simplificaciones. Se incorpora asimismo un mecanismo que permite acelerar la respuesta en caso necesario. Como parte del autopiloto, se define una estrategia para repartir el esfuerzo de control entre el canard y la cola. Esto se consigue mediante un controlador aumentado situado antes del bucle de optimización, que minimiza el esfuerzo total de control para maniobrar. Esta ley de alimentación directa mantiene al misil cerca de sus condiciones de equilibrio, garantizando una respuesta transitoria adecuada. El controlador no lineal elimina la respuesta de fase no-mínima característica de la cola. En esta Tesis se consideran dos diseños para el guiado y control, el control en Doble-Lazo y el control Integrado. En la aproximación de Doble-Lazo, el autopiloto se sitúa dentro de un bucle interior y se diseña independientemente del guiado, que conforma el bucle más exterior del control. Esta estructura asume que existe separación espectral entre los dos, esto es, que los tiempos de respuesta del autopiloto son mucho mayores que los tiempos característicos del guiado. En el estudio se combina el autopiloto desarrollado con una ley de guiado óptimo. Los resultados obtenidos demuestran que se consiguen aumentos muy importantes en las actuaciones frente a misiles con control canard o control en cola, y que la interceptación, cuando se lanza cerca del curso de colisión, se consigue desde cualquier ángulo alrededor del blanco. Para el misil de doble mando, la estrategia óptima resulta en utilizar el modo de control opuesto en la aproximación al blanco y utilizar el modo de desviación justo antes del impacto. Sin embargo la lógica de doble bucle no consigue el impacto cuando hay desviaciones importantes con respecto al curso de colisión. Una de las razones es que parte de la demanda de guiado se pierde, ya que el misil solo es capaz de modificar su aceleración lateral, y no tiene control sobre su aceleración axial, a no ser que incorpore un motor de empuje regulable. La hipótesis de separación mencionada, y que constituye la base del Doble-Bucle, puede no ser aplicable cuando la dinámica del misil es muy alta en las proximidades del blanco. Si se combinan el guiado y el autopiloto en un único bucle, la información de los estados del misil está disponible para el cálculo de la ley de guiado, y puede calcularse la estrategia optima de guiado considerando las capacidades y la actitud del misil. Una tercera contribución de la Tesis es la resolución de este segundo diseño, la integración no lineal del guiado y del autopiloto (IGA) para el misil de doble control. Aproximaciones anteriores en la literatura han planteado este sistema en ejes cuerpo, resultando en un sistema muy inestable debido al bajo amortiguamiento del misil en cabeceo y guiñada. Las simplificaciones que se tomaron también causan que el misil se deslice alrededor del blanco y no consiga la intercepción. En nuestra aproximación el problema se plantea en ejes inerciales y se recurre a la dinámica de los cuaterniones, eliminado estos inconvenientes. No se limita a la dinámica de corto periodo del misil, porque se construye incluyendo de modo explícito la velocidad dentro del bucle de optimización. La formulación resultante en el IGA es independiente de la maniobra del blanco, que sin embargo se ha de incluir en el cálculo del modelo en Doble-bucle. Un típico inconveniente de los sistemas integrados con controlador proporcional, es el problema de las escalas. Los errores de guiado dominan sobre los errores de posición del misil y saturan el controlador, provocando la pérdida del misil. Este problema se ha tratado aquí con un controlador aumentado previo al bucle de optimización, que define un estado de equilibrio local para el sistema integrado, que pasa a actuar como un regulador. Los criterios de actuaciones para el IGA son los mismos que para el sistema de Doble-Bucle. Sin embargo el problema matemático resultante es muy complejo. El problema óptimo para tiempo finito resulta en una ecuación diferencial de Riccati con condiciones terminales, que no puede resolverse. Mediante un cambio de variable y la introducción de una matriz de transición, este problema se transforma en una ecuación diferencial de Lyapunov que puede resolverse mediante métodos numéricos. La solución resultante solo es aplicable en un entorno cercano del blanco. Cuando la distancia entre misil y blanco es mayor, se desarrolla una solución aproximada basada en la solución de una ecuación algebraica de Riccati para cada paso de integración. Los resultados que se han obtenido demuestran, a través de análisis numéricos en distintos escenarios, que la solución integrada es mejor que el sistema de Doble-Bucle. Las trayectorias resultantes son muy distintas. El IGA preserva el guiado del misil y consigue maximizar el uso de la propulsión, consiguiendo la interceptación del blanco en menores tiempos de vuelo. El sistema es capaz de lograr el impacto donde el Doble-Bucle falla, y además requiere un orden menos de magnitud en la cantidad de cálculos necesarios. El efecto de los ruidos radar, datos discretos y errores del radomo se investigan. El IGA es más robusto, resultando menos afectado por perturbaciones que el Doble- Bucle, especialmente porque el núcleo de optimización en el IGA es independiente de la maniobra del blanco. La estimación de la maniobra del blanco es siempre imprecisa y contaminada por ruido, y degrada la precisión de la solución de Doble-Bucle. Finalmente, como una cuarta contribución, se demuestra que el misil con guiado IGA es capaz de realizar una maniobra de defensa contra un blanco que ataque por su cola, sólo con control aerodinámico. Las trayectorias estudiadas consideran una fase pre-programada de alta velocidad de giro, manteniendo siempre el misil dentro de su envuelta de vuelo. Este procedimiento no necesita recurrir a soluciones técnicamente más complejas como el control vectorial del empuje o control por chorro para ejecutar esta maniobra. En todas las demostraciones matemáticas se utiliza el producto de Kronecker como una herramienta practica para manejar las parametrizaciones dependientes de variables, que resultan en matrices de grandes dimensiones. ABSTRACT Future missions for air to air endo-atmospheric missiles require the interception of targets with higher speeds and more maneuverable, including forthcoming unmanned supersonic combat vehicles. The interception will need to be achieved from any angle and off-boresight launch conditions. One of the most significant discussions in missile technology today is how to satisfy these new operational requirements by increasing missile maneuvering capabilities and in parallel, through the development of more advanced guidance and control methods. This Thesis addresses these two objectives by proposing a novel optimal integrated guidance and autopilot design scheme, applicable to more maneuverable missiles with forward and rearward aerodynamic controls. A first insight of these results have been recently published in the Journal of Aerospace Engineering in April 2015, [Ibarrondo and Sanz-Aránguez, 2015]. The value of this integrated solution is that it allows the missile to comply with the aforementioned requirements only by applying aerodynamic control. The proposed design is compared against more traditional guidance and control approaches with positive results, achieving reduced control efforts and lower miss distances with the integrated logic even in the presence of noises. In this Thesis it will be demonstrated how the dual control missile, where canard and tail fins are both movable, can enhance the capabilities of an existing missile airframe. Compared to a tail missile, dual control only requires two additional servos to actuate the canards in pitch and yaw. The tail section will be responsible to maintain the missile stabilized in roll, like in a classic tail missile. The additional complexity is that the vortices shed from the canard propagate downstream where they interact with the tail surfaces, altering the tail expected control characteristics. These aerodynamic phenomena must be properly described, as a preliminary step, with high enough precision for advanced guidance and control studies. As a first contribution we have developed a full analytical model of the nonlinear aerodynamics of a missile with dual control, including the characterization of this cross-control coupling effect. This development has been produced from a theoretical model validated with reliable practical data obtained from wind tunnel experiments available in the scientific literature, complement with computer fluid dynamics and semi-experimental methods. There are two modes of operating a missile with forward and rear controls, ”divert” and ”opposite” modes. In divert mode, controls are deflected in the same direction, generating an increment in direct lift and missile translation. Response is fast, but in this mode, dual control missiles may have difficulties in achieving large angles of attack and high level of lateral accelerations. When controls are deflected in opposite directions (opposite mode) the missile airframe rotates and the body angle of attack is increased to generate greater accelerations in steady-state, although the response time is larger. With the aero-model, a state dependent parametrization of the dual control missile short term dynamics can be obtained. Due to the cross-coupling effect, the open loop dynamics for the dual control missile is not linearly dependent of the fin positions. The short term missile dynamics are blended with the servo system to obtain an extended autopilot model, where the response is linear with the control fins turning rates, that will be the control variables. The flight control loop is optimized to achieve the maneuver required by the guidance law without exceeding any of the missile aerodynamic or mechanical limitations. The specific aero-limitations and relevant performance indicators for the dual control are set as part of the analysis. A second contribution of this Thesis is the development of a step-tracking multi-input autopilot that integrates non-linear aerodynamics. The designed dual control missile autopilot is a full three dimensional autopilot, where roll, pitch and yaw are integrated, calculating command inputs simultaneously. The autopilot control gains are state dependent, and calculated at each integration step solving a matrix Riccati equation of order 21x21. The resulting gains are sub-optimal as a full solution for the Hamilton-Jacobi-Bellman equation cannot be resolved in practical terms and some simplifications are taken. Acceleration mechanisms with an λ-shift is incorporated in the design. As part of the autopilot, a strategy is defined for proper allocation of control effort between canard and tail channels. This is achieved with an augmented feed forward controller that minimizes the total control effort of the missile to maneuver. The feedforward law also maintains the missile near trim conditions, obtaining a well manner response of the missile. The nonlinear controller proves to eliminate the non-minimum phase effect of the tail. Two guidance and control designs have been considered in this Thesis: the Two- Loop and the Integrated approaches. In the Two-Loop approach, the autopilot is placed in an inner loop and designed separately from an outer guidance loop. This structure assumes that spectral separation holds, meaning that the autopilot response times are much higher than the guidance command updates. The developed nonlinear autopilot is linked in the study to an optimal guidance law. Simulations are carried on launching close to collision course against supersonic and highly maneuver targets. Results demonstrate a large boost in performance provided by the dual control versus more traditional canard and tail missiles, where interception with the dual control close to collision course is achieved form 365deg all around the target. It is shown that for the dual control missile the optimal flight strategy results in using opposite control in its approach to target and quick corrections with divert just before impact. However the Two-Loop logic fails to achieve target interception when there are large deviations initially from collision course. One of the reasons is that part of the guidance command is not followed, because the missile is not able to control its axial acceleration without a throttleable engine. Also the separation hypothesis may not be applicable for a high dynamic vehicle like a dual control missile approaching a maneuvering target. If the guidance and autopilot are combined into a single loop, the guidance law will have information of the missile states and could calculate the most optimal approach to the target considering the actual capabilities and attitude of the missile. A third contribution of this Thesis is the resolution of the mentioned second design, the non-linear integrated guidance and autopilot (IGA) problem for the dual control missile. Previous approaches in the literature have posed the problem in body axes, resulting in high unstable behavior due to the low damping of the missile, and have also caused the missile to slide around the target and not actually hitting it. The IGA system is posed here in inertial axes and quaternion dynamics, eliminating these inconveniences. It is not restricted to the missile short term dynamic, and we have explicitly included the missile speed as a state variable. The IGA formulation is also independent of the target maneuver model that is explicitly included in the Two-loop optimal guidance law model. A typical problem of the integrated systems with a proportional control law is the problem of scales. The guidance errors are larger than missile state errors during most of the flight and result in high gains, control saturation and loss of control. It has been addressed here with an integrated feedforward controller that defines a local equilibrium state at each flight point and the controller acts as a regulator to minimize the IGA states excursions versus the defined feedforward state. The performance criteria for the IGA are the same as in the Two-Loop case. However the resulting optimization problem is mathematically very complex. The optimal problem in a finite-time horizon results in an irresoluble state dependent differential Riccati equation with terminal conditions. With a change of variable and the introduction of a transition matrix, the equation is transformed into a time differential Lyapunov equation that can be solved with known numerical methods in real time. This solution results range limited, and applicable when the missile is in a close neighborhood of the target. For larger ranges, an approximate solution is used, obtained from solution of an algebraic matrix Riccati equation at each integration step. The results obtained show, by mean of several comparative numerical tests in diverse homing scenarios, than the integrated approach is a better solution that the Two- Loop scheme. Trajectories obtained are very different in the two cases. The IGA fully preserves the guidance command and it is able to maximize the utilization of the missile propulsion system, achieving interception with lower miss distances and in lower flight times. The IGA can achieve interception against off-boresight targets where the Two- Loop was not able to success. As an additional advantage, the IGA also requires one order of magnitude less calculations than the Two-Loop solution. The effects of radar noises, discrete radar data and radome errors are investigated. IGA solution is robust, and less affected by radar than the Two-Loop, especially because the target maneuvers are not part of the IGA core optimization loop. Estimation of target acceleration is always imprecise and noisy and degrade the performance of the two-Loop solution. The IGA trajectories are such that minimize the impact of radome errors in the guidance loop. Finally, as a fourth contribution, it is demonstrated that the missile with IGA guidance is capable of performing a defense against attacks from its rear hemisphere, as a tail attack, only with aerodynamic control. The studied trajectories have a preprogrammed high rate turn maneuver, maintaining the missile within its controllable envelope. This solution does not recur to more complex features in service today, like vector control of the missile thrust or side thrusters. In all the mathematical treatments and demonstrations, the Kronecker product has been introduced as a practical tool to handle the state dependent parametrizations that have resulted in very high order matrix equations.

Telemetría de vehículos FSAE con microcontrolador PIC32 y transceptor de radio CC1101

Quizás el campo de las telecomunicaciones sea uno de los campos en el que más se ha progresado en este último siglo y medio, con la ayuda de otros campos de la ciencia y la técnica tales como la computación, la física electrónica, y un gran número de disciplinas, que se han utilizado estos últimos 150 años en conjunción para mejorarse unas con la ayuda de otras. Por ejemplo, la química ayuda a comprender y mejorar campos como la medicina, que también a su vez se ve mejorada por los progresos en la electrónica creados por los físicos y químicos, que poseen herramientas más potentes para calcular y simular debido a los progresos computacionales. Otro de los campos que ha sufrido un gran avance en este último siglo es el de la automoción, aunque estancados en el motor de combustión, los vehículos han sufrido enormes cambios debido a la irrupción de los avances en la electrónica del automóvil con multitud de sistemas ya ampliamente integrados en los vehículos actuales. La Formula SAE® o Formula Student es una competición de diseño, organizada por la SAE International (Society of Automotive Engineers) para estudiantes de universidades de todo el mundo que promueve la ingeniería a través de una competición donde los miembros del equipo diseñan, construyen, desarrollan y compiten en un pequeño y potente monoplaza. En el ámbito educativo, evitando el sistema tradicional de clases magistrales, se introducen cambios en las metodologías de enseñanza y surge el proyecto de la Fórmula Student para lograr una mejora en las acciones formativas, que permitan ir incorporando nuevos objetivos y diseñar nuevas situaciones de aprendizaje que supongan una oportunidad para el desarrollo de competencias de los alumnos, mejorar su formación como ingenieros y contrastar sus progresos compitiendo con las mejores universidades del mundo. En este proyecto se pretende dotar a los alumnos de las escuelas de ingeniería de la UPM que desarrollan el vehículo de FSAE de una herramienta de telemetría con la que evaluar y probar comportamiento del vehículo de FSAE junto con sus subsistemas que ellos mismos diseñan, con el objetivo de evaluar el comportamiento, introducir mejoras, analizar resultados de una manera más rápida y cómoda, con el objetivo de poder progresar más rápidamente en su desarrollo, recibiendo y almacenando una realimentación directa e instantánea del funcionamiento mediante la lectura de los datos que circulan por el bus CAN del vehículo. También ofrece la posibilidad de inyectar datos a los sistemas conectados al bus CAN de manera remota. Se engloba en el conjunto de proyectos de la FSAE, más concretamente en los basados en la plataforma PIC32 y propone una solución conjunta con otros proyectos o también por sí sola. Para la ejecución del proyecto se fabricó una placa compuesta de dos placas de circuito impreso, la de la estación base que envía comandos, instrucciones y datos para inyectar en el bus CAN del vehículo mediante radiofrecuencia y la placa que incorpora el vehículo que envía las tramas que circulan por el bus CAN del vehículo con los identificadores deseados, ejecuta los comandos recibidos por radiofrecuencia y salva las tramas CAN en una memoria USB o SD Card. Las dos PCBs constituyen el hardware del proyecto. El software se compone de dos programas. Un programa para la PCB del vehículo que emite los datos a la estación base, codificado en lenguaje C con ayuda del entorno de desarrollo MPLAB de Microchip. El otro programa hecho con LabView para la PCB de la estación base que recibe los datos provenientes del vehículo y los interpreta. Se propone un hardware y una capa o funciones de software para los microcontroladores PIC32 (similar al de otros proyectos del FSAE) para la transmisión de las tramas del bus CAN del vehículo de manera inalámbrica a una estación base, capaz de insertar tramas en el bus CAN del vehículo enviadas desde la estación base. También almacena estas tramas CAN en un dispositivo USB o SD Card situado en el vehículo. Para la transmisión de los datos se hizo un estudio de las frecuencias de transmisión, la legislación aplicable y los tipos de transceptores. Se optó por utilizar la banda de radiofrecuencia de uso común ISM de 433MHz mediante el transceptor integrado CC110L de Texas Instruments altamente configurable y con interfaz SPI. Se adquirieron dos parejas de módulos compatibles, con amplificador de potencia o sin él. LabView controla la estación que recoge las tramas CAN vía RF y está dotada del mismo transceptor de radio junto con un puente de comunicaciones SPI-USB, al que se puede acceder de dos diferentes maneras, mediante librerías dll, o mediante NI-VISA con transferencias RAW-USB. La aplicación desarrollada posee una interfaz configurable por el usuario para la muestra de los futuros sensores o actuadores que se incorporen en el vehículo y es capaz de interpretar las tramas CAN, mostrarlas, gráfica, numéricamente y almacenar esta información, como si fuera el cuadro de instrumentos del vehículo. Existe una limitación de la velocidad global del sistema en forma de cuello de botella que se crea debido a las limitaciones del transceptor CC110L por lo que si no se desea filtrar los datos que se crean necesarios, sería necesario aumentar el número de canales de radio para altas ocupaciones del bus CAN. Debido a la pérdida de relaciones con el INSIA, no se pudo probar de manera real en el propio vehículo, pero se hicieron pruebas satisfactorias (hasta 1,6 km) con una configuración de tramas CAN estándar a una velocidad de transmisión de 1 Mbit/s y un tiempo de bit de 1 microsegundo. El periférico CAN del PIC32 se programará para cumplir con estas especificaciones de la ECU del vehículo, que se presupone que es la MS3 Sport de Bosch, de la que LabView interpretará las tramas CAN recibidas de manera inalámbrica. Para poder probar el sistema, ha sido necesario reutilizar el hardware y adaptar el software del primer prototipo creado, que emite tramas CAN preprogramadas con una latencia también programable y que simulará al bus CAN proporcionando los datos a transmitir por el sistema que incorpora el vehículo. Durante el desarrollo de este proyecto, en las etapas finales, el fabricante del puente de comunicaciones SPI-USB MCP2210 liberó una librería (dll) compatible y sin errores, por lo que se nos ofrecía una oportunidad interesante para la comparación de las velocidades de acceso al transceptor de radio, que se presuponía y se comprobó más eficiente que la solución ya hecha mediante NI-VISA. ABSTRACT. The Formula SAE competition is an international university applied to technological innovation in vehicles racing type formula, in which each team, made up of students, should design, construct and test a prototype each year within certain rules. The challenge of FSAE is that it is an educational project farther away than a master class. The goal of the present project is to make a tool for other students to use it in his projects related to FSAE to test and improve the vehicle, and, the improvements that can be provided by the electronics could be materialized in a victory and win the competition with this competitive advantage. A telemetry system was developed. It sends the data provided by the car’s CAN bus through a radio frequency transceiver and receive commands to execute on the system, it provides by a base station on the ground. Moreover, constant verification in real time of the status of the car or data parameters like the revolutions per minute, pressure from collectors, water temperature, and so on, can be accessed from the base station on the ground, so that, it could be possible to study the behaviour of the vehicle in early phases of the car development. A printed circuit board, composed of two boards, and two software programs in two different languages, have been developed, and built for the project implementation. The software utilized to design the PCB is Orcad10.5/Layout. The base station PCB on a PC receives data from the PCB connected to the vehicle’s CAN bus and sends commands like set CAN filters or masks, activate data logger or inject CAN frames. This PCB is connected to a PC via USB and contains a bridge USB-SPI to communicate with a similar transceiver on the vehicle PCB. LabView controls this part of the system. A special virtual Instrument (VI) had been created in order to add future new elements to the vehicle, is a dashboard, which reads the data passed from the main VI and represents them graphically to studying the behaviour of the car on track. In this special VI other alums can make modifications to accommodate the data provided from the vehicle CAN’s bus to new elements on the vehicle, show or save the CAN frames in the form or format they want. Two methods to access to SPI bus of CC110l RF transceiver over LabView have been developed with minimum changes between them. Access through NI-VISA (Virtual Instrument Software Architecture) which is a standard for configuring, programming, USB interfaces or other devices in National Instruments LabView. And access through DLL (dynamic link library) supplied by the manufacturer of the bridge USB-SPI, Microchip. Then the work is done in two forms, but the dll solution developed shows better behaviour, and increase the speed of the system because has less overload of the USB bus due to a better efficiency of the dll solution versus VISA solution. The PCB connected to the vehicle’s CAN bus receives commands from the base station PCB on a PC, and, acts in function of the command or execute actions like to inject packets into CAN bus or activate data logger. Also sends over RF the CAN frames present on the bus, which can be filtered, to avoid unnecessary radio emissions or overflowing the RF transceiver. This PCB consists of two basic pieces: A microcontroller with 32 bit architecture PIC32MX795F512L from Microchip and the radio transceiver integrated circuit CC110l from Texas Instruments. The PIC32MX795F512L has an integrated CAN and several peripherals like SPI controllers that are utilized to communicate with RF transceiver and SD Card. The USB controller on the PIC32 is utilized to store CAN data on a USB memory, and change notification peripheral is utilized like an external interrupt. Hardware for other peripherals is accessible. The software part of this PCB is coded in C with MPLAB from Microchip, and programming over PICkit 3 Programmer, also from Microchip. Some of his libraries have been modified to work properly with this project and other was created specifically for this project. In the phase for RF selection and design is made a study to clarify the general aspects of regulations for the this project in order to understand it and select the proper band, frequency, and radio transceiver for the activities developed in the project. From the different options available it selects a common use band ICM, with less regulation and free to emit with restrictions and disadvantages like high occupation. The transceiver utilized to transmit and receive the data CC110l is an integrated circuit which needs fewer components from Texas Instruments and it can be accessed through SPI bus. Basically is a state machine which changes his state whit commands received over an SPI bus or internal events. The transceiver has several programmable general purpose Inputs and outputs. These GPIOs are connected to PIC32 change notification input to generate an interrupt or connected to GPIO to MCP2210 USB-SPI bridge to inform to the base station for a packet received. A two pair of modules of CC110l radio module kit from different output power has been purchased which includes an antenna. This is to keep away from fabrication mistakes in RF hardware part or designs, although reference design and gerbers files are available on the webpage of the chip manufacturer. A neck bottle is present on the complete system, because the maximum data rate of CC110l transceiver is a half than CAN bus data rate, hence for high occupation of CAN bus is recommendable to filter the data or add more radio channels, because the buffers can’t sustain this load along the time. Unfortunately, during the development of the project, the relations with the INSIA, who develops the vehicle, was lost, for this reason, will be made impossible to test the final phases of the project like integration on the car, final test of integration, place of the antenna, enclosure of the electronics, connectors selection, etc. To test or evaluate the system, it was necessary to simulate the CAN bus with a hardware to feed the system with entry data. An early hardware prototype was adapted his software to send programed CAN frames at a fixed data rate and certain timing who simulate several levels of occupation of the CAN Bus. This CAN frames emulates the Bosch ECU MS3 Sport.

A review of clinical trial designs used to detect a disease-modifying effect of drug therapy in Alzheimer's disease and Parkinson's disease

Acknowledgements This article presents independent research funded by the National Institute for Health Research (NIHR) under its Programme Grants for Applied Research Programme (Grant Reference Number RP-PG-0707-10124). The views expressed in this article are those of the authors and not necessarily those of the NHS, the NIHR or the Department of Health. The funders had no role in study design, data collection, data analysis, data interpretation, writing of the report or for the decision to submit for publication.

The sulfur controller-2 negative regulatory gene of Neurospora crassa encodes a protein with beta-transducin repeats.

The sulfur regulatory system of Neurospora crassa is composed of a set of structural genes involved in sulfur catabolism controlled by a genetically defined set of trans-acting regulatory genes. These sulfur regulatory genes include cys-3+, which encodes a basic region-leucine zipper transcriptional activator, and the negative regulatory gene scon-2+. We report here that the scon-2+ gene encodes a polypeptide of 650 amino acids belonging to the expanding beta-transducin family of eukaryotic regulatory proteins. Specifically, SCON2 protein contains six repeated G beta-homologous domains spanning the C-terminal half of the protein. SCON2 represents the initial filamentous fungal protein identified in the beta-transducin group. Additionally, SCON2 exhibits a specific amino-terminal domain that potentially defines another subfamily of beta-transducin homologs. Expression of the scon-2+ gene has been examined using RNA hybridization and gel mobility-shift analysis. The dependence of scon-2+ expression on CYS3 function and the binding of CYS3 to the scon-2+ promoter indicate the presence of an important control loop within the N. crassa sulfur regulatory circuit involving CYS3 activation of scon-2+ expression. On the basis of the presence of beta-transducin repeats, the crucial role of SCON2 in the signal-response pathway triggered by sulfur limitation may be mediated by protein-protein interactions.

Exception or extension? : reorienting the Peacock Room among James McNeill Whistler's interior designs

"Although famous for his paintings and etchings today, James McNeill Whistler (1834-1903) was also an important interior designer in the nineteenth-century British Aesthetic movement. Whistler‘s most famous and only extant interior design is Harmony in Blue and Gold: The Peacock Room (1876-77). It is also his most puzzling interior. Long considered an exception to the rule of Whistler‘s other interiors, the Peacock Room has often been overlooked in the few studies of the artist‘s interior designs"

What We Are Learning About the Diverse Backgrounds of Academic Library Users: An Overview of Research Designs and Methods in Information Behaviour Studies

Academic libraries increasingly serve a more diverse population of users not only in regard to race and ethnicity, but also to age, gender, language, sexual orientation, and national and cultural backgrounds. This papers reports the findings of the study that explored information behaviour research as a potential source of information about diversity of academic library users and examined the relationship between the use of different research designs and data collection methods and the information gathered about users’ diverse backgrounds. The study found that information behaviour research offers limited insight into the diversity of academic library users. The choice of a research design was not critical but the use of multiple data collection played a role in gathering information about culturally diverse users.

Mixed Public-Private Enterprises in Europe: Economic Theory and an Empirical Analysis of Italian Water Utilities. Bruges European Economic Research (BEER) Papers 4/July 2006

Mixed enterprises, which are entities jointly owned by the public and private sector, are spreading all over Europe in local utilities. Well aware that in the vast majority of cases the preference of local authorities towards such governance structure is determined by practical reasons rather than by the ambition to implement new regulatory designs (an alternative to the typical “external” regulation), our purpose is to confer some scientific value to this phenomenon which has not been sufficiently investigated in the economic literature. This paper aims at proposing an economic analysis of mixed enterprises, especially of the specific configuration in which the public partner acts as controller and the private one (or “industrial” partner) as service provider. We suggest that the public service concession to mixed enterprises could embody, under certain conditions, a noteworthy substitute to the traditional public provision and the concession to totally private enterprises, as it can push regulated operators to outperform and limit the risk of private opportunism. The starting point of the entire analysis is that ownership allows the (public) owner to gather more information about the actual management of the firm, according to property rights theory. Following this stream of research, we conclude that under certain conditions mixed enterprises could significantly reduce asymmetric information between regulators and regulated firms by implementing a sort of “internal” regulation. With more information, in effect, the public authority (as owner/controller of the regulated firm, but also as member of the regulatory agency) can stimulate the private operator to be more efficient and can monitor it more effectively with respect to the fulfilment of contractual obligations (i.e., public service obligations, quality standards, etc.). Moreover, concerning the latter function, the board of directors of the mixed enterprise can be the suitable place where public and private representatives (respectively, welfare and profit maximisers) can meet to solve all disputes arising from incomplete contracts, without recourse to third parties. Finally, taking into account that a disproportionate public intervention in the “private” administration (or an ineffective protection of the general interest) would imply too many drawbacks, we draw some policy implications that make an equitable debate on the board of the firm feasible. Some empirical evidence is taken from the Italian water sector.

Field-based models for low speed switched reluctance machine designs

Trabalho apresentado na Conferência CPE-POWERENG 2016, 29 junho a 01 de julho 2016, Bydgoszcz, Polónia

Entwicklung eines anpassungsfähigen Internet-Designs für die Firma „blueways“, unter Berücksichtigung des User- Verhaltens und Aspekten der Usability

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Bridge deck designs for railing impacts. Final report.

Texas State Department of Highways and Public Transportation, Transportation Planning Division, Austin

The larger forms of musical composition; an exhaustive explanation of the variations, rondos, and sonata designs, for the general student of musical analysis, and for the special student of structural composition,

"A sequel to the Homophonic forms and Applied counterpoint."--Pref.