Realizzazione di un sistema per l’incremento della leggibilità dei contenuti Web Testuali

Nel primo capitolo parleremo dell'accessibilità ai siti web siccome con la crescita dei contenuti multimediali e dei contenuti dinamici, non vengono sempre presi in causa le disabilità che una persona può avere nel visualizzare determinati contenuti. Si tratterà di crescita del web 2.0 e nascita del web 3.0. La transcodifica dei contenuti e i problemi che ogni persona in base alla sua disabilità può riscontrare usando apparecchi differenti per l'accesso ai dati. Parleremo dell'evoluzione dell'uso dei siti in versione mobile cosi da fare un paragono con l'usabilità tra desktop e mobile. Nel secondo capitolo andremo ad analizzare tutte le specifiche che siamo andati a prendere in considerazione per lo sviluppo di questa estensione. Guarderemo quali sono le motivazioni che ci hanno portato allo sviluppo di un'estensione di questo tipo. Verranno anche descritte tutte le scelte progettuali prese in via di sviluppo per migliorare l'usabilità e l'utilizzo dei dati raccolti, per fornire un servizio più efficiente all'utente. Nel terzo capitolo andremo a spiegare tutta l'implementazione effettuata per ExTraS con tutte le funzionalità considerate e scelte in base ai problemi più importanti di accessibilità attualmente riscontrati nel mondo del web da persone con diversi gradi di disabilità. Le principali disabilità che vengono prese in considerazione per l'utilizzo di questo addon sono persone che soffrono di ipovisione, daltonismo. L'ultimo paragrafo di questo capitolo descriverà test effettuati con utenti reali e con utenti simulati. Il test con utenti simulati è stato effettuato grazie al lavoro di tesi effettuato da Alberto Fariselli il quale ha integrato ExTraS creando un simulatore basato sul Q-learning.

Predictive control of hybrid vehicle powertrain for intelligent energy management

This thesis studies the minimization of the fuel consumption for a Hybrid Electric Vehicle (HEV) using Model Predictive Control (MPC). The presented MPC – based controller calculates an optimal sequence of control inputs to a hybrid vehicle using the measured plant outputs, the current dynamic states, a system model, system constraints, and an optimization cost function. The MPC controller is developed using Matlab MPC control toolbox. To evaluate the performance of the presented controller, a power-split hybrid vehicle, 2004 Toyota Prius, is selected. The vehicle uses a planetary gear set to combine three power components, an engine, a motor, and a generator, and transfer energy from these components to the vehicle wheels. The planetary gear model is developed based on the Willis’s formula. The dynamic models of the engine, the motor, and the generator, are derived based on their dynamics at the planetary gear. The MPC controller for HEV energy management is validated in the MATLAB/Simulink environment. Both the step response performance (a 0 – 60 mph step input) and the driving cycle tracking performance are evaluated. Two standard driving cycles, Urban Dynamometer Driving Schedule (UDDS) and Highway Fuel Economy Driving Schedule (HWFET), are used in the evaluation tests. For the UDDS and HWFET driving cycles, the simulation results, the fuel consumption and the battery state of charge, using the MPC controller are compared with the simulation results using the original vehicle model in Autonomie. The MPC approach shows the feasibility to improve vehicle performance and minimize fuel consumption.

STUDY OF SPARK IGNITION ENGINE COMBUSTION MODEL FOR THE ANALYSIS OF CYCLIC VARIATION AND COMBUSTION STABILITY AT LEAN OPERATING CONDITIONS

A fundamental combustion model for spark-ignition engine is studied in this report. The model is implemented in SIMULINK to simulate engine outputs (mass fraction burn and in-cylinder pressure) under various engine operation conditions. The combustion model includes a turbulent propagation and eddy burning processes based on literature [1]. The turbulence propagation and eddy burning processes are simulated by zero-dimensional method and the flame is assumed as sphere. To predict pressure, temperature and other in-cylinder variables, a two-zone thermodynamic model is used. The predicted results of this model match well with the engine test data under various engine speeds, loads, spark ignition timings and air fuel mass ratios. The developed model is used to study cyclic variation and combustion stability at lean (or diluted) combustion conditions. Several variation sources are introduced into the combustion model to simulate engine performance observed in experimental data. The relations between combustion stability and the introduced variation amount are analyzed at various lean combustion levels.

HOUSEHOLD SOLAR POWER SYSTEM

Photovoltaic power has become one of the most popular research area in new energy field. In this report, the case of household solar power system is presented. Based on the Matlab environment, the simulation is built by using Simulink and SimPowerSystem. There are four parts in a household solar system, solar cell, MPPT system, battery and power consumer. Solar cell and MPPT system are been studied and analyzed individually. The system with MPPT generates 30% more energy than the system without MPPT. After simulating the household system, it is can be seen that the power which generated by the system is 40.392 kWh per sunny day. By combining the power generated by the system and the price of the electric power, 8.42 years are need for the system to achieve a balance of income and expenditure when weather condition is considered.

Soft-computing based visual control for unmanned vehicles

El objetivo principal de esta Tesis es extender la utilización del “Soft- Computing” para el control de vehículos sin piloto utilizando visión. Este trabajo va más allá de los típicos sistemas de control utilizados en entornos altamente controlados, demonstrando la fuerza y versatilidad de la lógica difusa (Fuzzy Logic) para controlar vehículos aéreos y terrestres en un abanico de applicaciones diferentes. Para esta Tesis se ha realizado un gran número de pruebas reales en las cuales los controladores difusos han manejado una plataforma visual “pan-and-tilt”, un helicoptero, un coche comercial y hasta dos tipos de quadrirotores. El uso del método de optimización “Cross-Entropy” ha sido utilizado para mejorar el comportamiento de algunos de los controladores borrosos. Todos los controladores difusos presentados en ésta Tesis han sido implementados utilizando un código desarrollado por el candidato para tal efecto, llamado MOFS (Miguel Olivares’ Fuzzy Software). Diferentes algoritmos visuales han sido utilizados para adquirir la informaci´on visual del entorno, “Cmashift”, descomposición de la homografía y detección de marcas de realidad aumentada, entre otros. Dicha información visual ha sido utilizada como entrada de los controladores difusos para comandar los vehículos en las diferentes applicaciones autonomas. El volante de un vehículo comercial ha sido controlado para realizar pruebas de conducción autónoma en condiciones de tráfico similares a las de una ciudad. El sistema ha llegado a completar con éxito pruebas de más de 6 km sin ninguna interacción humana, mediante el seguimiento de una línea pintada en el suelo. El limitado campo visual del sistema no ha sido impedimento para alcanzar velocidades de hasta 48 km/h y ser guiado autonomamente en curvas de radio reducido. Objetos estáticos y móviles han sido seguidos desde un helicoptero no tripulado, mediante el control de una plataforma visual “pan-and-tilt”. ´Éste mismo helicoptero ha sido controlado completamente para su aterrizaje autonomo, mediante el control del movimiento lateral (roll), horizontal (pitch) y de altitud. El seguimiento de objetos volantes ha sido resulto mediante el control horizontal (pitch) y de orientación (heading) de un quadrirotor. Para tareas de evitación de obstáculos se ha implementado un controlador difuso para el manejo de la orientación (heading) de un quadrirotor. En el campo de la optimización de controladores se ha aportado al estado del arte una extensión del uso del método “Cross-Entropy”. Está Tesis presenta una novedosa implementación de dicho método para la optimización de las ganancias, la posición y medida de los conjuntos de las funciones de pertenecia y el peso de las reglas para mejorar el comportamiento de un controlador difuso. Dichos procesos de optimización se han realizado utilizando “ROS” y “Matlab Simulink” para obtener mejores resultados para la evitación de colisiones con vehículos aéreos no tripulados. Ésta Tesis demuestra que los controladores implementados con lógica difusa son altamente capaces de controlador sistemas sin tener en cuenta el modelo del vehículo a controlador en entornos altamente perturbables con un sensor de bajo coste como es una cámara. El ruido presentes causado por los cambios de iluminación en la adquisición de imágenes y la alta incertidumbre en la detección visual han sido manejados satisfactoriamente por ésta técnica de de “Soft-Computing” para distintas aplicaciones tanto con vehículos aéreos como terrestres.

Simulation of AC, DC, and AC-DC coupled mini-grids. In search of the most efficient system

Renewable energy hybrid systems and mini-grids for electrification of rural areas are known to be reliable and more cost efficient than grid extension or only-diesel based systems. However, there is still some uncertainty in some areas, for example, which is the most efficient way of coupling hybrid systems: AC, DC or AC-DC? With the use of Matlab/Simulink a mini-grid that connects a school, a small hospital and an ecotourism hostel has been modelled. This same mini grid has been coupled in the different possible ways and the system’s efficiency has been studied. In addition, while keeping the consumption constant, the generation sources and the consumption profile have been modified and the effect on the efficiency under each configuration has also been analysed. Finally different weather profiles have been introduced and, again, the effect on the efficiency of each system has been observed.

Analysis of WCET in an experimental satellite software development.

This paper describes a case study in WCET analysis of an on-board spacecraft software system. The attitude control system of UPMSat-2, an experimental micro-satellite which is scheduled to be launched in 2013, is used for an experiment on analysing the worst-case execution time of code automatically generated from a Simulink model. In order to properly test the code, a hardware-in-the-loop configuration with a simulation model of the spacecraft environment has been used as a test bench. The code has been analysed with RapiTime, with some modifications to the original instrumentation routines, in order to take into account the particularities of the test configuration. Results from the experiment are described and commented in the paper.

A platform for real-time control education with LEGO MINDSTORMS.

A set of software development tools for building real-time control systems on a simple robotics platform is described in the paper. The tools are being used in a real-time systems course as a basis for student projects. The development platform is a low-cost PC running GNU/Linux, and the target system is LEGO MINDSTORMS NXT, thus keeping the cost of the laboratory low. Real-time control software is developed using a mixed paradigm. Functional code for control algorithms is automatically generated in C from Simulink models. This code is then integrated into a concurrent, real-time software architecture based on a set of components written in Ada. This approach enables the students to take advantage of the high-level, model-oriented features that Simulink oers for designing control algorithms, and the comprehensive support for concurrency and real-time constructs provided by Ada.

Sistema de instrumentação e controle para células a combustível

Este trabajo presenta un estudio sobre el funcionamiento y aplicaciones de las células de combustible de membrana tipo PEM, o de intercambio de protones, alimentadas con hidrógeno puro y oxigeno obtenido de aire comprimido. Una vez evaluado el proceso de dichas células y las variables que intervienen en el mismo, como presión, humedad y temperatura, se presenta una variedad de métodos para la instrumentación de tales variables así como métodos y sistemas para la estabilidad y control de las mismas, en torno a los valores óptimos para una mayor eficacia en el proceso. Tomando como variable principal a controlar la temperatura del proceso, y exponiendo los valores concretos en torno a 80 grados centígrados entre los que debe situarse, es realizado un modelo del proceso de calentamiento y evolución de la temperatura en función de la potencia del calentador resistivo en el dominio de la frecuencia compleja, y a su vez implementado un sistema de medición mediante sensores termopar de tipo K de respuesta casi lineal. La señal medida por los sensores es amplificada de manera diferencial mediante amplificadores de instrumentación INA2126, y es desarrollado un algoritmo de corrección de error de unión fría (error producido por la inclusión de nuevos metales del conector en el efecto termopar). Son incluidos los datos de test referentes al sistema de medición de temperatura , incluyendo las desviaciones o error respecto a los valores ideales de medida. Para la adquisición de datos y implementación de algoritmos de control, es utilizado un PC con el software Labview de National Instruments, que permite una programación intuitiva, versátil y visual, y poder realizar interfaces de usuario gráficas simples. La conexión entre el hardware de instrumentación y control de la célula y el PC se realiza mediante un interface de adquisición de datos USB NI 6800 que cuenta con un amplio número de salidas y entradas analógicas. Una vez digitalizadas las muestras de la señal medida, y corregido el error de unión fría anteriormente apuntado, es implementado en dicho software un controlador de tipo PID ( proporcional-integral-derivativo) , que se presenta como uno de los métodos más adecuados por su simplicidad de programación y su eficacia para el control de este tipo de variables. Para la evaluación del comportamiento del sistema son expuestas simulaciones mediante el software Matlab y Simulink determinando por tanto las mejores estrategias para desarrollar el control PID, así como los posibles resultados del proceso. En cuanto al sistema de calentamiento de los fluidos, es empleado un elemento resistor calentador, cuya potencia es controlada mediante un circuito electrónico compuesto por un detector de cruce por cero de la onda AC de alimentación y un sistema formado por un elemento TRIAC y su circuito de accionamiento. De manera análoga se expone el sistema de instrumentación para la presión de los gases en el circuito, variable que oscila en valores próximos a 3 atmosferas, para ello es empleado un sensor de presión con salida en corriente mediante bucle 4-20 mA, y un convertidor simple corriente a tensión para la entrada al sistema de adquisición de datos. Consecuentemente se presenta el esquema y componentes necesarios para la canalización, calentamiento y humidificación de los gases empleados en el proceso así como la situación de los sensores y actuadores. Por último el trabajo expone la relación de algoritmos desarrollados y un apéndice con información relativa al software Labview. ABTRACT This document presents a study about the operation and applications of PEM fuel cells (Proton exchange membrane fuel cells), fed with pure hydrogen and oxygen obtained from compressed air. Having evaluated the process of these cells and the variables involved on it, such as pressure, humidity and temperature, there is a variety of methods for implementing their control and to set up them around optimal values for greater efficiency in the process. Taking as primary process variable the temperature, and exposing its correct values around 80 degrees centigrade, between which must be placed, is carried out a model of the heating process and the temperature evolution related with the resistive heater power on the complex frequency domain, and is implemented a measuring system with thermocouple sensor type K performing a almost linear response. The differential signal measured by the sensor is amplified through INA2126 instrumentation amplifiers, and is developed a cold junction error correction algorithm (error produced by the inclusion of additional metals of connectors on the thermocouple effect). Data from the test concerning the temperature measurement system are included , including deviations or error regarding the ideal values of measurement. For data acquisition and implementation of control algorithms, is used a PC with LabVIEW software from National Instruments, which makes programming intuitive, versatile, visual, and useful to perform simple user interfaces. The connection between the instrumentation and control hardware of the cell and the PC interface is via a USB data acquisition NI 6800 that has a large number of analog inputs and outputs. Once stored the samples of the measured signal, and correct the error noted above junction, is implemented a software controller PID (proportional-integral-derivative), which is presented as one of the best methods for their programming simplicity and effectiveness for the control of such variables. To evaluate the performance of the system are presented simulations using Matlab and Simulink software thereby determining the best strategies to develop PID control, and possible outcomes of the process. As fluid heating system, is employed a heater resistor element whose power is controlled by an electronic circuit comprising a zero crossing detector of the AC power wave and a system consisting of a Triac and its drive circuit. As made with temperature variable it is developed an instrumentation system for gas pressure in the circuit, variable ranging in values around 3 atmospheres, it is employed a pressure sensor with a current output via 4-20 mA loop, and a single current to voltage converter to adequate the input to the data acquisition system. Consequently is developed the scheme and components needed for circulation, heating and humidification of the gases used in the process as well as the location of sensors and actuators. Finally the document presents the list of algorithms and an appendix with information about Labview software.

Flutter margin with non-linearities: real-time prediction of flutter onset speed

The present article shows a procedure to predict the flutter speed based on real-time tuning of a quasi non-linear aeroelastic model. A two-dimensional non-linear (freeplay) aeroeslastic model is implemented inMatLab/Simulink with incompressible aerodynamic conditions. A comparison with real compressible conditions is provided. Once the numerical validation is accomplished, a parametric aeroelastic model is built in order to describe the proposed procedure and contribute to reduce the number of flight hours needed to expand the flutter envelope.

Static analysis of WCET in a satellite software subsystem

This paper describes the authors? experience with static analysis of both WCET and stack usage of a satellite on-board software subsystem. The work is a continuation of a previous case study that used a dynamic WCET analysis tool on an earlier version of the same software system. In particular, the AbsInt aiT tool has been evaluated by analysing both C and Ada code generated by Simulink within the UPMSat-2 project. Some aspects of the aiT tool, specifically those dealing with SPARC register windows, are compared to another static analysis tool, Bound-T. The results of the analysis are discussed, and some conclusions on the use of static WCET analysis tools on the SPARC architecture are commented in the paper.

Predicción de la velocidad crítica de flameo mediante el uso de modelos aeroelásticos extrapolados en tiempo real con datos de vuelo

La Aeroelasticidad fue definida por Arthur Collar en 1947 como "el estudio de la interacción mutua entre fuerzas inerciales, elásticas y aerodinámicas actuando sobre elementos estructurales expuestos a una corriente de aire". Actualmente, esta definición se ha extendido hasta abarcar la influencia del control („Aeroservoelasticidad‟) e, incluso, de la temperatura („Aerotermoelasticidad‟). En el ámbito de la Ingeniería Aeronáutica, los fenómenos aeroelásticos, tanto estáticos (divergencia, inversión de mando) como dinámicos (flameo, bataneo) son bien conocidos desde los inicios de la Aviación. Las lecciones aprendidas a lo largo de la Historia Aeronáutica han permitido establecer criterios de diseño destinados a mitigar la probabilidad de sufrir fenómenos aeroelásticos adversos durante la vida operativa de una aeronave. Adicionalmente, el gran avance experimentado durante esta última década en el campo de la Aerodinámica Computacional y en la modelización aeroelástica ha permitido mejorar la fiabilidad en el cálculo de las condiciones de flameo de una aeronave en su fase de diseño. Sin embargo, aún hoy, los ensayos en vuelo siguen siendo necesarios para validar modelos aeroelásticos, verificar que la aeronave está libre de inestabilidades aeroelásticas y certificar sus distintas envolventes. En particular, durante el proceso de expansión de la envolvente de una aeronave en altitud/velocidad, se requiere predecir en tiempo real las condiciones de flameo y, en consecuencia, evitarlas. A tal efecto, en el ámbito de los ensayos en vuelo, se han desarrollado diversas metodologías que predicen, en tiempo real, las condiciones de flameo en función de condiciones de vuelo ya verificadas como libres de inestabilidades aeroelásticas. De entre todas ellas, aquella que relaciona el amortiguamiento y la velocidad con un parámetro específico definido como „Margen de Flameo‟ (Flutter Margin), permanece como la técnica más común para proceder con la expansión de Envolventes en altitud/velocidad. No obstante, a pesar de su popularidad y facilidad de aplicación, dicha técnica no es adecuada cuando en la aeronave a ensayar se hallan presentes no-linealidades mecánicas como, por ejemplo, holguras. En particular, en vuelos de ensayo dedicados específicamente a expandir la envolvente en altitud/velocidad, las condiciones de „Oscilaciones de Ciclo Límite‟ (Limit Cycle Oscillations, LCOs) no pueden ser diferenciadas de manera precisa de las condiciones de flameo, llevando a una determinación excesivamente conservativa de la misma. La presente Tesis desarrolla una metodología novedosa, basada en el concepto de „Margen de Flameo‟, que permite predecir en tiempo real las condiciones de „Ciclo Límite‟, siempre que existan, distinguiéndolas de las de flameo. En una primera parte, se realiza una revisión bibliográfica de la literatura acerca de los diversos métodos de ensayo existentes para efectuar la expansión de la envolvente de una aeronave en altitud/velocidad, el efecto de las no-linealidades mecánicas en el comportamiento aeroelástico de dicha aeronave, así como una revisión de las Normas de Certificación civiles y militares respecto a este tema. En una segunda parte, se propone una metodología de expansión de envolvente en tiempo real, basada en el concepto de „Margen de Flameo‟, que tiene en cuenta la presencia de no-linealidades del tipo holgura en el sistema aeroelástico objeto de estudio. Adicionalmente, la metodología propuesta se valida contra un modelo aeroelástico bidimensional paramétrico e interactivo programado en Matlab. Para ello, se plantean las ecuaciones aeroelásticas no-estacionarias de un perfil bidimensional en la formulación espacio-estado y se incorpora la metodología anterior a través de un módulo de análisis de señal y otro módulo de predicción. En una tercera parte, se comparan las conclusiones obtenidas con las expuestas en la literatura actual y se aplica la metodología propuesta a resultados experimentales de ensayos en vuelo reales. En resumen, los principales resultados de esta Tesis son: 1. Resumen del estado del arte en los métodos de ensayo aplicados a la expansión de envolvente en altitud/velocidad y la influencia de no-linealidades mecánicas en la determinación de la misma. 2. Revisión de la normas de Certificación Civiles y las normas Militares en relación a la verificación aeroelástica de aeronaves y los límites permitidos en presencia de no-linealidades. 3. Desarrollo de una metodología de expansión de envolvente basada en el Margen de Flameo. 4. Validación de la metodología anterior contra un modelo aeroelástico bidimensional paramétrico e interactivo programado en Matlab/Simulink. 5. Análisis de los resultados obtenidos y comparación con resultados experimentales. ABSTRACT Aeroelasticity was defined by Arthur Collar in 1947 as “the study of the mutual interaction among inertia, elastic and aerodynamic forces when acting on structural elements surrounded by airflow”. Today, this definition has been updated to take into account the Controls („Aeroservoelasticity‟) and even the temperature („Aerothermoelasticity‟). Within the Aeronautical Engineering, aeroelastic phenomena, either static (divergence, aileron reversal) or dynamic (flutter, buzz), are well known since the early beginning of the Aviation. Lessons learned along the History of the Aeronautics have provided several design criteria in order to mitigate the probability of encountering adverse aeroelastic phenomena along the operational life of an aircraft. Additionally, last decade improvements experienced by the Computational Aerodynamics and aeroelastic modelization have refined the flutter onset speed calculations during the design phase of an aircraft. However, still today, flight test remains as a key tool to validate aeroelastic models, to verify flutter-free conditions and to certify the different envelopes of an aircraft. Specifically, during the envelope expansion in altitude/speed, real time prediction of flutter conditions is required in order to avoid them in flight. In that sense, within the flight test community, several methodologies have been developed to predict in real time flutter conditions based on free-flutter flight conditions. Among them, the damping versus velocity technique combined with a Flutter Margin implementation remains as the most common technique used to proceed with the envelope expansion in altitude/airspeed. However, although its popularity and „easy to implement‟ characteristics, several shortcomings can adversely affect to the identification of unstable conditions when mechanical non-linearties, as freeplay, are present. Specially, during test flights devoted to envelope expansion in altitude/airspeed, Limits Cycle Oscillations (LCOs) conditions can not be accurately distinguished from those of flutter and, in consequence, it leads to an excessively conservative envelope determination. The present Thesis develops a new methodology, based on the Flutter Margin concept, that enables in real time the prediction of the „Limit Cycle‟ conditions, whenever they exist, without degrading the capability of predicting the flutter onset speed. The first part of this Thesis presents a review of the state of the art regarding the test methods available to proceed with the envelope expansion of an aircraft in altitude/airspeed and the effect of mechanical non-linearities on the aeroelastic behavior. Also, both civil and military regulations are reviewed with respect aeroelastic investigation of air vehicles. The second part of this Thesis proposes a new methodology to perform envelope expansion in real time based on the Flutter Margin concept when non-linearities, as freeplay, are present. Additionally, this methodology is validated against a Matlab/Slimulink bidimensional aeroelastic model. This model, parametric and interactive, is formulated within the state-space field and it implements the proposed methodology through two main real time modules: A signal processing module and a prediction module. The third part of this Thesis compares the final conclusions derived from the proposed methodology with those stated by the flight test community and experimental results. In summary, the main results provided by this Thesis are: 1. State of the Art review of the test methods applied to envelope expansion in altitude/airspeed and the influence of mechanical non-linearities in its identification. 2. Review of the main civil and military regulations regarding the aeroelastic verification of air vehicles and the limits set when non-linearities are present. 3. Development of a methodology for envelope expansion based on the Flutter Margin concept. 4. A Matlab/Simulink 2D-[aeroelastic model], parametric and interactive, used as a tool to validate the proposed methodology. 5. Conclusions driven from the present Thesis and comparison with experimental results.

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.

Teaching and evaluating mechanical vibrations with Matlab®

The study of the response of mechanical systems to external excitations, even in the simplest cases, involves solving second-order ordinary differential equations or systems thereof. Finding the natural frequencies of a system and understanding the effect of variations of the excitation frequencies on the response of the system are essential when designing mechanisms [1] and structures [2]. However, faced with the mathematical complexity of the problem, students tend to focus on the mathematical resolution rather than on the interpretation of the results. To overcome this difficulty, once the general theoretical problem and its solution through the state space [3] have been presented, Matlab®[4] and Simulink®[5] are used to simulate specific situations. Without them, the discussion of the effect of slight variations in input variables on the outcome of the model becomes burdensome due to the excessive calculation time required. Conversely, with the help of those simulation tools, students can easily reach practical conclusions and their evaluation can be based on their interpretation of results and not on their mathematical skills

Diseño del sistema de potencia para un satélite de órbita baja(LEO) = Design of a Low Earth Orbit (LEO) satellite power subsystem

Este documento contiene el proceso de prediseño y cálculo de un satélite de observación terrestre mediante imágenes fotográficas. El principal objetivo del proyecto es el diseño detallado del subsistema de potencia del satélite y a validación de un modelo de funcionamiento del sistema de potencia de las placas solares que alimentan al mismo y mediante la herramienta Simulink. La primera parte consiste en un diseño breve de los subsistemas y parámetros más importantes del satélite tales como el Sistema de Control de Actitud, Sistema de Control Térmico y Sistema de Comunicaciones, además de la estructura del satélite, la órbita en la que se encontrará, el lanzador que se usará para situarlo en órbita y la cámara que llevara a bordo para la captación de imágenes. La segunda parte trata del diseño del subsistema de potencia de una manera más detallada y de su simulación mediante una herramienta diseñada en el programa MATLAB con la herramienta Simulink. Se pretende usar la herramienta para simular el comportamiento del subsistema de potencia de un satélite conocido que será el UPMSat-2.