Influencia del tratamiento "a fuego" en las características del estuco tradicional con cal = Influence of treatment "by fire" in the characteristics of traditional lime stucco

Esta investigación avanza en el intento de recuperar la técnica tradicional del estuco a fuego, paradigma de la decoración de espacios interiores hasta la mitad del s. XX por sus imitaciones marmóreas de gran calidad. Para ejecutarlos se utilizaban morteros de cal con áridos de mármol, pigmentos minerales y grasas; con estos materiales se preparaban y tendían las masas, se pintaban al fresco y se terminaban con el paso de una herramienta metálica caliente. Como sucede con otras técnicas, el paso del tiempo ha difuminado los conocimientos sobre la materia, haciendo muy difícil la conservación o restauración de los ejemplos en nuestro patrimonio. A partir de la escasa bibliografía existente se ha recuperado el proceso, sometiendo las muestras elaboradas a diferentes ensayos que han caracterizado el acabado final,tanto en sus características intrínsecas como en las que le son conferidas al proteger finalmente las muestras con una capa de cera, tal y como se realizaba tradicionalmente.---ABSTRACT---This research advances in the attempt to recover the traditional technique of stucco by fire; paradigm of indoor decoration until half of 20th century due to its high quality marbled imitations. On its implementation process, it was used lime mortars with marble aggregates, mineral pigments and greases. With these materials, masses were prepared and extended into the walls, they were painted in fresco and ended with the passage of a heated metal tool. As with any other technique, the time passing over has blurred the knowledge on the subject, making very difficult the preservation or restoration of examples in our heritage. Despite of the limited literature, the process has been recovered; subjecting the samples prepared at different trials that have characterized the finished, both in its merits and its conferred characteristics by finally protecting the samples with a layer of wax, as was done traditionally.

Characteristics of the turbulent/nonturbulent interface in boundary layers, jets and shear-free turbulence

The characteristics of turbulent/nonturbulent interfaces (TNTI) from boundary layers, jets and shear-free turbulence are compared using direct numerical simulations. The TNTI location is detected by assessing the volume of turbulent flow as function of the vorticity magnitude and is shown to be equivalent to other procedures using a scalar field. Vorticity maps show that the boundary layer contains a larger range of scales at the interface than in jets and shear-free turbulence where the change in vorticity characteristics across the TNTI is much more dramatic. The intermittency parameter shows that the extent of the intermittency region for jets and boundary layers is similar and is much bigger than in shear-free turbulence, and can be used to compute the vorticity threshold defining the TNTI location. The statistics of the vorticity jump across the TNTI exhibit the imprint of a large range of scales, from the Kolmogorov micro-scale to scales much bigger than the Taylor scale. Finally, it is shown that contrary to the classical view, the low-vorticity spots inside the jet are statistically similar to isotropic turbulence, suggesting that engulfing pockets simply do not exist in jets

Comparison of fermentation characteristics and bacterial diversity in the rumen of sheep and batch cultures of rumen microorganisms

The objective of the current study was to assess how closely batch cultures (BC) of rumen microorganisms can mimic the dietary differences in fermentation characteristics found in the rumen, and to analyse changes in bacterial diversity over the in vitro incubation period. Four ruminally and duodenally cannulated sheep were fed four diets having forage : concentrate ratios (FCR) of 70 : 30 or 30 : 70, with either alfalfa hay or grass hay as forage. Rumen fluid from each sheep was used to inoculate BC containing the same diet fed to the donor sheep, and the main rumen fermentation parameters were determined after 24 h of incubation. There were differences between BC and sheep in the magnitude of most measured parameters, but BC detected differences among diets due to forage type similar to those found in sheep. In contrast, BC did not reproduce the dietary differences due to FCR found in sheep for pH, degradability of neutral detergent fibre and total volatile fatty acid (VFA) concentrations. There were differences between systems in the magnitude of most determined parameters and BC showed higher pH values and NH3–N concentrations, but lower fibre degradability and VFA and lactate concentrations compared with sheep. There were significant relationships between in vivo and in vitro values for molar proportions of acetate, propionate and butyrate, and the acetate : propionate ratio. The automated ribosomal intergenic spacer analysis (ARISA) of 16S ribosomal deoxyribonucleic acid showed that FCR had no effect on bacterial diversity either in the sheep rumen fluid used as inoculum (IN) or in BC samples. In contrast, bacterial diversity was greater with alfalfa hay diets than those with grass hay in the IN, but was unaffected by forage type in the BC. Similarity index between the bacterial communities in the inocula and those in the BC ranged from 67·2 to 74·7%, and was unaffected by diet characteristics. Bacterial diversity was lower in BC than in the inocula with 14 peaks out of a total of 181 detected in the ARISA electropherograms never appearing in BC samples, which suggests that incubation conditions in the BC may have caused a selection of some bacterial strains. However, each BC sample showed the highest similarity index with its corresponding rumen IN, which highlights the importance of using rumen fluid from donors fed a diet similar to that being incubated in BC when conducting in vitro experiments.

Time evolution of frequency components In a chaotic digital signal

The type of signals obtained has conditioned chaos analysis tools. Almost in every case, they have analogue characteristics. But in certain cases, a chaotic digital signal is obtained and theses signals need a different approach than conventional analogue ones. The main objective of this paper will be to present some possible approaches to the study of this signals and how information about their characteristics may be obtained in the more straightforward possible way. We have obtained digital chaotic signals from an Optical Logic Cell with some feedback between output and one of the possible control gates. This chaos has been reported in several papers and its characteristics have been employed as a possible method to secure communications and as a way to encryption. In both cases, the influence of some perturbation in the transmission medium gave problems both for the synchronization of chaotic generators at emitter and receiver and for the recovering of information data. A proposed way to analyze the presence of some perturbation is to study the noise contents of transmitted signal and to implement a way to eliminate it. In our present case, the digital signal will be converted to a multilevel one by grouping bits in packets of 8 bits and applying conventional methods of time-frequency analysis to them. The results give information about the change in signals characteristics and hence some information about the noise or perturbations present. Equivalent representations to the phase and to the Feigenbaum diagrams for digital signals are employed in this case.

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.

Magnetic Attitude Control System for a Small Satellite. Impact on the Thermal Performance

El principal objetivo de la tesis es estudiar el acoplamiento entre los subsistemas de control de actitud y de control térmico de un pequeño satélite, con el fin de buscar la solución a los problemas relacionados con la determinación de los parámetros de diseño. Se considera la evolución de la actitud y de las temperaturas del satélite bajo la influencia de dos estrategias de orientación diferentes: 1) estabilización magnética pasiva de la orientación (PMAS, passive magnetic attitude stabilization), y 2) control de actitud magnético activo (AMAC, active magnetic attitude control). En primer lugar se presenta el modelo matemático del problema, que incluye la dinámica rotacional y el modelo térmico. En el problema térmico se considera un satélite cúbico modelizado por medio de siete nodos (seis externos y uno interno) aplicando la ecuación del balance térmico. Una vez establecido el modelo matemático del problema, se estudia la evolución que corresponde a las dos estrategias mencionadas. La estrategia PMAS se ha seleccionado por su simplicidad, fiabilidad, bajo coste, ahorrando consumo de potencia, masa coste y complejidad, comparado con otras estrategias. Se ha considerado otra estrategia de control que consigue que el satélite gire a una velocidad requerida alrededor de un eje deseado de giro, pudiendo controlar su dirección en un sistema inercial de referencia, ya que frecuentemente el subsistema térmico establece requisitos de giro alrededor de un eje del satélite orientado en una dirección perpendicular a la radiación solar incidente. En relación con el problema térmico, para estudiar la influencia de la velocidad de giro en la evolución de las temperaturas en diversos puntos del satélite, se ha empleado un modelo térmico linealizado, obtenido a partir de la formulación no lineal aplicando un método de perturbaciones. El resultado del estudio muestra que el tiempo de estabilización de la temperatura y la influencia de las cargas periódicas externas disminuye cuando aumenta la velocidad de giro. Los cambios de temperatura se reducen hasta ser muy pequeños para velocidades de rotación altas. En relación con la estrategia PMAC se ha observado que a pesar de su uso extendido entre los micro y nano satélites todavía presenta problemas que resolver. Estos problemas están relacionados con el dimensionamiento de los parámetros del sistema y la predicción del funcionamiento en órbita. Los problemas aparecen debido a la dificultad en la determinación de las características magnéticas de los cuerpos ferromagnéticos (varillas de histéresis) que se utilizan como amortiguadores de oscilaciones en los satélites. Para estudiar este problema se presenta un modelo analítico que permite estimar la eficiencia del amortiguamiento, y que se ha aplicado al estudio del comportamiento en vuelo de varios satélites, y que se ha empleado para comparar los resultados del modelo con los obtenidos en vuelo, observándose que el modelo permite explicar satisfactoriamente el comportamiento registrado. ABSTRACT The main objective of this thesis is to study the coupling between the attitude control and thermal control subsystems of a small satellite, and address the solution to some existing issues concerning the determination of their parameters. Through the thesis the attitude and temperature evolution of the satellite is studied under the influence of two independent attitude stabilization and control strategies: (1) passive magnetic attitude stabilization (PMAS), and (2) active magnetic attitude control (AMAC). In this regard the mathematical model of the problem is explained and presented. The mathematical model includes both the rotational dynamics and the thermal model. The thermal model is derived for a cubic satellite by solving the heat balance equation for 6 external and 1 internal nodes. Once established the mathematical model of the problem, the above mentioned attitude strategies were applied to the system and the temperature evolution of the 7 nodes of the satellite was studied. The PMAS technique has been selected to be studied due to its prevalent use, simplicity, reliability, and cost, as this strategy significantly saves the overall power, weight, cost, and reduces the complexity of the system compared to other attitude control strategies. In addition to that, another control law that provides the satellite with a desired spin rate along a desired axis of the satellite, whose direction can be controlled with respect to the inertial reference frame is considered, as the thermal subsystem of a satellite usually demands a spin requirement around an axis of the satellite which is positioned perpendicular to the direction of the coming solar radiation. Concerning the thermal problem, to study the influence of spin rate on temperature evolution of the satellite a linear approach of the thermal model is used, which is based on perturbation theory applied to the nonlinear differential equations of the thermal model of a spacecraft moving in a closed orbit. The results of this study showed that the temperature stabilization time and the periodic influence of the external thermal loads decreases by increasing the spin rate. However, the changes become insignificant for higher values of spin rate. Concerning the PMAS strategy, it was observed that in spite of its extended application to micro and nano satellites, still there are some issues to be solved regarding this strategy. These issues are related to the sizing of its system parameters and predicting the in-orbit performance. The problems were found to be rooted in the difficulties that exist in determining the magnetic characteristics of the ferromagnetic bodies (hysteresis rods) that are applied as damping devices on-board satellites. To address these issues an analytic model for estimating their damping efficiency is proposed and applied to several existing satellites in order to compare the results with their respective in-flight data. This model can explain the behavior showed by these satellites.

Electron transport and azimuthal oscillations in hall thrusters

The Hall Effect Thruster (HET) is a type of satellite electric propulsion device initially developed in the 1960’s independently by USA and the former USSR. The development continued in the shadow during the 1970’s in the Soviet Union to reach a mature status from the technological point of view in the 1980’s. In the 1990’s the advanced state of this Russian technology became known in western countries, which rapidly restarted the analysis and development of modern Hall thrusters. Currently, there are several companies in USA, Russia and Europe manufacturing Hall thrusters for operational use. The main applications of these thrusters are low-thrust propulsion of interplanetary probes, orbital raising of satellites and stationkeeping of geostationary satellites. However, despite the well proven in-flight experience, the physics of the Hall Thruster are not completely understood yet. Over the last two decades large efforts have been dedicated to the understanding of the physics of Hall Effect thrusters. However, the so-called anomalous diffusion, short name for an excessive electron conductivity along the thruster, is not yet fully understood as it cannot be explained with classical collisional theories. One commonly accepted explanation is the existence of azimuthal oscillations with correlated plasma density and electric field fluctuations. In fact, there is experimental evidence of the presence of an azimuthal oscillation in the low frequency range (a few kHz). This oscillation, usually called spoke, was first detected empirically by Janes and Lowder in the 1960s. More recently several experiments have shown the existence of this type of oscillation in various modern Hall thrusters. Given the frequency range, it is likely that the ionization is the cause of the spoke oscillation, like for the breathing mode oscillation. In the high frequency range (a few MHz), electron-drift azimuthal oscillations have been detected in recent experiments, in line with the oscillations measured by Esipchuk and Tilinin in the 1970’s. Even though these low and high frequency azimuthal oscillations have been known for quite some time already, the physics behind them are not yet clear and their possible relation with the anomalous diffusion process remains an unknown. This work aims at analysing from a theoretical point of view and via computer simulations the possible relation between the azimuthal oscillations and the anomalous electron transport in HET. In order to achieve this main objective, two approaches are considered: local linear stability analyses and global linear stability analyses. The use of local linear stability analyses shall allow identifying the dominant terms in the promotion of the oscillations. However, these analyses do not take into account properly the axial variation of the plasma properties along the thruster. On the other hand, global linear stability analyses do account for these axial variations and shall allow determining how the azimuthal oscillations are promoted and their possible relation with the electron transport.

Efficiency of hysteresis rods in small spacecraft attitude stabilization

A semiempirical method for predicting the damping efficiency of hysteresis rods on-board small satellites is presented. It is based on the evaluation of dissipating energy variation of different ferromagnetic materials for two different rod shapes: thin film and circular cross-section rods, as a function of their elongation. Based on this formulation, an optimum design considering the size of hysteresis rods, their cross section shape, and layout has been proposed. Finally, the formulation developed was applied to the case of four existing small satellites, whose corresponding in-flight data are published. A good agreement between the estimated rotational speed decay time and the in-flight data has been observed.

Simulation of thermal performance of glazing in architecture using scale models = Simulación del comportamiento térmico de los acristalamientos en la arquitectura mediante modelos a escala

El propósito de esta tesis es estudiar la aproximación a los fenómenos de transporte térmico en edificación acristalada a través de sus réplicas a escala. La tarea central de esta tesis es, por lo tanto, la comparación del comportamiento térmico de modelos a escala con el correspondiente comportamiento térmico del prototipo a escala real. Los datos principales de comparación entre modelo y prototipo serán las temperaturas. En el primer capítulo del Estado del Arte de esta tesis se hará un recorrido histórico por los usos de los modelos a escala desde la antigüedad hasta nuestro días. Dentro de éste, en el Estado de la Técnica, se expondrán los beneficios que tiene su empleo y las dificultades que conllevan. A continuación, en el Estado de la Investigación de los modelos a escala, se analizarán artículos científicos y tesis. Precisamente, nos centraremos en aquellos modelos a escala que son funcionales. Los modelos a escala funcionales son modelos a escala que replican, además, una o algunas de las funciones de sus prototipos. Los modelos a escala pueden estar distorsionados o no. Los modelos a escala distorsionados son aquellos con cambios intencionados en las dimensiones o en las características constructivas para la obtención de una respuesta específica por ejemplo, replicar el comportamiento térmico. Los modelos a escala sin distorsión, o no distorsionados, son aquellos que mantienen, en la medida de lo posible, las proporciones dimensionales y características constructivas de sus prototipos de referencia. Estos modelos a escala funcionales y no distorsionados son especialmente útiles para los arquitectos ya que permiten a la vez ser empleados como elementos funcionales de análisis y como elementos de toma de decisiones en el diseño constructivo. A pesar de su versatilidad, en general, se observará que se han utilizado muy poco estos modelos a escala funcionales sin distorsión para el estudio del comportamiento térmico de la edificación. Posteriormente, se expondrán las teorías para el análisis de los datos térmicos recogidos de los modelos a escala y su aplicabilidad a los correspondientes prototipos a escala real. Se explicarán los experimentos llevados a cabo, tanto en laboratorio como a intemperie. Se han realizado experimentos con modelos sencillos cúbicos a diferentes escalas y sometidos a las mismas condiciones ambientales. De estos modelos sencillos hemos dado el salto a un modelo reducido de una edificación acristalada relativamente sencilla. Los experimentos consisten en ensayos simultáneos a intemperie del prototipo a escala real y su modelo reducido del Taller de Prototipos de la Escuela Técnica Superior de Arquitectura de Madrid (ETSAM). Para el análisis de los datos experimentales hemos aplicado las teorías conocidas, tanto comparaciones directas como el empleo del análisis dimensional. Finalmente, las simulaciones nos permiten comparaciones flexibles con los datos experimentales, por ese motivo, hemos utilizado tanto programas comerciales como un algoritmo de simulación desarrollado ad hoc para esta investigación. Finalmente, exponemos la discusión y las conclusiones de esta investigación. Abstract The purpose of this thesis is to study the approximation to phenomena of heat transfer in glazed buildings through their scale replicas. The central task of this thesis is, therefore, the comparison of the thermal performance of scale models without distortion with the corresponding thermal performance of their full-scale prototypes. Indoor air temperatures of the scale model and the corresponding prototype are the data to be compared. In the first chapter on the State of the Art, it will be shown a broad vision, consisting of a historic review of uses of scale models, from antiquity to our days. In the section State of the Technique, the benefits and difficulties associated with their implementation are presented. Additionally, in the section State of the Research, current scientific papers and theses on scale models are reviewed. Specifically, we focus on functional scale models. Functional scale models are scale models that replicate, additionally, one or some of the functions of their corresponding prototypes. Scale models can be distorted or not. Scale models with distortion are considered scale models with intentional changes, on one hand, in dimensions scaled unevenly and, on the other hand, in constructive characteristics or materials, in order to get a specific performance for instance, a specific thermal performance. Consequently, scale models without distortion, or undistorted scale models scaled evenly, are those replicating, to the extent possible, without distortion, the dimensional proportions and constructive configurations of their prototypes of reference. These undistorted and functional scale models are especially useful for architects because they can be used, simultaneously, as functional elements of analysis and as decision-making elements during the design. Although they are versatile, in general, it is remarkable that these types of models are used very little for the study of the thermal performance of buildings. Subsequently, the theories related to the analysis of the experimental thermal data collected from the scale models and their applicability to the corresponding full-scale prototypes, will be explained. Thereafter, the experiments in laboratory and at outdoor conditions are detailed. Firstly, experiments carried out with simple cube models at different scales are explained. The prototype larger in size and the corresponding undistorted scale model have been subjected to same environmental conditions in every experimental test. Secondly, a step forward is taken carrying out some simultaneous experimental tests of an undistorted scale model, replica of a relatively simple lightweight and glazed building construction. This experiment consists of monitoring the undistorted scale model of the prototype workshop located in the School of Architecture (ETSAM) of the Technical University of Madrid (UPM). For the analysis of experimental data, known related theories and resources are applied, such as, direct comparisons, statistical analyses, Dimensional Analysis and last, but not least important, simulations. Simulations allow us, specifically, flexible comparisons with experimental data. Here, apart the use of the simulation software EnergyPlus, a simulation algorithm is developed ad hoc for this research. Finally, the discussion and conclusions of this research are exposed.

Impact of N2 plasma power and duration on AlGaN/GaN HEMT

urface treatments have been recently shown to play an active role in electrical characteristics in AlGaN/GaN HEMTs, in particular during the passivation processing [1-4]. However, the responsible mechanisms are partially unknown and further studies are demanding. The effects of power and time N2 plasma pre-treatment prior to SiN deposition using PE-CVD (plasma enhanced chemical vapour deposition) on GaN and AlGaN/GaN HEMT have been investigated. The low power (60 W) plasma pre-treatment was found to improve the electronic characteristics in GaN based HEMT devices, independently of the time duration up to 20 min. In contrast, high power (150 and 210 W) plasma pretreatment showed detrimental effects in the electronic properties (Fig. 1), increasing the sheet resistance of the 2DEG, decreasing the 2DEG charge density in AlGaN/GaN HEMTs, transconductance reduction and decreasing the fT and fmax values up to 40% respect to the case using 60 W N2 plasma power. Although AFM (atomic force microscopy) results showed AlGaN and GaN surface roughness is not strongly affected by the N2-plasma, KFM (Kelvin force microscopy) surface analysis shows significant changes in the surface potential, trending to increase its values as the plasma power is higher. The whole results point at energetic ions inducing polarization-charge changes that affect dramatically to the 2-DEG charge density and the final characteristics of the HEMT devices. Therefore, we conclude that AlGaN surface is strongly sensitive to N2 plasma power conditions, which turn to be a key factor to achieve a good surface preparation prior to SiN passivation.

Non-linear gain - look-up table based approach for modeling a family of DC to DC converters based on transient response analysis

The purpose of this work is to propose a structure for simulating power systems using behavioral models of nonlinear DC to DC converters implemented through a look-up table of gains. This structure is specially designed for converters whose output impedance depends on the load current level, e.g. quasi-resonant converters. The proposed model is a generic one whose parameters can be obtained by direct measuring the transient response at different operating points. It also includes optional functionalities for modeling converters with current limitation and current sharing in paralleling characteristics. The pusposed structured also allows including aditional characteristics of the DC to DC converter as the efficency as a function of the input voltage and the output current or overvoltage and undervoltage protections. In addition, this proposed model is valid for overdamped and underdamped situations.

Aeronautical Information Geoservices

Aeronautical charts underlie the representation of aeronautic geographic information that supports pilots in flight. Nevertheless, charts become complex due to the high density of data and the different kinds that support each phase of flight. These features make difficult using them on board. After conducting a study that aims to understand and to evaluate pilot’s needs related to Geographic Information, it is proposed a solution to implement a platform based on geographic information standards (OGC, ISO) and supported by a distributed Web architecture. This platform facilitates the use, retrieval, updating of information and its exchange among different institutions through private and public users. As a first element to ensure interoperability and the harmonisation of information, we propose an aeronautical metadata profile that sets guidelines and elements for its description. This profile meets the standards set by ICAO, Eurocontrol and ISO. The platform offers three levels of access to data through different types of devices and user profiles. This paper suggests an alternative and reliable way for distributing aeronautical geoinformation, focusing on specific functions or displaying and querying.

Geoservices for Aeronautical Navigation

Aeronautical charts underlie the representation of aeronautic geographic information that supports pilots in flight. Nevertheless, the charts become complex due to the high density of data and the different kinds of charts that support each phase of flight. These features make difficult using them on board. After conducting a study, with civil Spaniard pilots, that aims to understand and to evaluate their needs related to Geographic Information, it is proposed a solution to implement a platform based on geographic information standards (OGC, ISO) and supported by a distributed Web architecture. This platform facilitates the use, retrieval, updating of information and its exchange among different institutions through private and public users. As a first element to ensure interoperability of information, we suggest an aeronautical metadata profile that sets guidelines and elements for its description. The metadata profile meets the standards set by ICAO, Eurocontrol and ISO. The platform offers three levels of access to data through different types of devices and user profiles. Thus, aeronautical institutions could edit data while pilot is on board accessing digital aeronautical charts through a laptop or Table PC. This paper suggests an alternative and reliable way for distributing aeronautical geoinformation, focusing on specific functions or displaying and querying.

Fundamentación del conjunto tractor-apero para la labor de surcado y su influencia en el consumo energético en cultivos de raíces y tubérculos

El cumplimiento de los objetivos agrotécnicos de los cultivos de raíces y tubérculos exige que la labor de surcado configure un caballón que permita el trabajo de los posteriores aperos que participan en las demás labores de cultivo. En la agricultura cubana se emplean diversos tipos de surcadores que difieren en las características de los elementos aporcadores. Este hecho afecta a la capacidad de trabajo del conjunto tractor-apero y por extensión en el consumo de combustible y el rendimiento del cultivo. El objetivo de este trabajo ha sido fundamentar el empleo del apero más adecuado para la labor de surcado en cultivos de raíces y tubérculos (patata, boniato, yuca) en Fluvisoles, teniendo en cuenta el comportamiento de las dimensiones y forma del caballón, cualidades tecnológicas explotativas del conjunto tractor-apero, consumo energético del proceso productivo y el rendimiento agrícola. Los tratamientos considerados estuvieron determinados por la utilización del surcador fertilizador IIMA-BALDAN 4.500 (T1), y los surcadores aporcadores SA-5 (T2) y SA-3 (T3). En los tres tratamientos se alcanzó un perfil de la sección transversal del caballón de configuración cóncavo-convexo. El surcador BALDAN logró el mejor comportamiento de los indicadores tecnológico-explotativos lo que se tradujo en la mayor capacidad de trabajo de 1,36 ha h-1 y el menor consumo de combustible de 5,38 L ha-1. Este mismo tratamiento proporcionó el mayor rendimiento medio de los cultivos superando en un 43,2% al del surcador SA-5 y en un 57,9% al del surcador SA-3. Desde el punto de vista energético T1, obtuvo una mejor eficiencia energética superior en un 43,5% a la del tratamiento T2, y en un 57,1% a la del tratamiento T3. ABSTRACT The achievement of agrotechnical objectives in the cultivation of roots and tubers demands the plow through activity creates a ridge to allow the work of subsequent farming tools participating in other cultivation works. In Cuban Agriculture various kinds of furrowers are used which differ in the characteristics of their earth up elements. This fact affects work capacity of the tractor-farming tool combination and by extension to fuel consumption and cultivation yield. The aim of this work has been to support the use of the most accurate farming tool in the plow through activity for the cultivation of roots and tubers (potato, sweet potato, cassava) in Fluvisoils, taking into account the behaviour of the ridge´s dimensions and shape, technologic-explotative qualities of the tractor-farming tool combination, energy consumption of the productive process and agricultural yield. The treatments considered were determined by the use of fertlizing furrower IIMA-BALDAN 4.500 (T1), and the earth up furrowers SA-5 (T2) and SA-3 (T3). During the three treatments a transverse section profile of the ridge under concave-convex configuration was obtained. The furrower BALDAN achieved the best behaviour of the technologic-explotative indicators, which was translated into the largest work capacity of 1,36 ha h-1 and the smallest fuel consumption of 5,38 L ha-1. This treatment also provided the biggest average yield of the cultivation, overcoming in a 43,2% the furrower SA-5 and furrower SA-3 in a 57,9%. From the energetic point of view T1 gained better energetic efficiency than treatment T2 in a 43,5% and treatment T3 in a 57,1%.

Análisis biomecánico del segmento de la carrera a pie de la competición en triatlón

El principal objetivo de la presente investigación fue el conocer el perfil de rendimiento técnico de los triatletas, desde un punto de vista biomecánica, en el segmento carrera a pie durante la competición en triatlón. Asimismo, como el genero y el nivel deportivo del triatleta podrían influir en su respuesta motriz durante la competicion. Para ello, se necesitaba desarrollar y validar una técnica experimental que fuera lo suficientemente precisa (validez interna), con una alta fiabilidad y con una gran validez externa (ecologica) debido al entorno de la competicion. La muestra la formaron un total de 64 deportistas: 32 triatletas participantes en la Copa del Mundo de Triatlon de Madrid-2008 (16 hombres y 16 mujeres) y 32 triatletas participantes en el Clasificatorio del Campeonato de Espana Elite (16 hombres y 16 mujeres). El análisis de la técnica de carrera de los deportistas se realizo mediante un sistema fotogramétrico en 2d que permitió calcular las coordenadas (x,y) de los centros articulares con un error de 1.66% en el eje x y de un 2.10% en el eje y. Las imágenes fueron obtenidas por una cámara que filmaba el movimiento en un plano antero-posterior del triatleta. Algoritmos basados en la DLT (Abdel-Aziz & Karara, 1971) permitieron conocer las coordenadas reales a partir de las coordenadas digitalizadas en el plano y posteriormente las distintas variables analizadas. El análisis biomecánica de la carrera se realizo en 4 ocasiones diferentes durante la competición, correspondiendo con cada una de las vueltas de 2,5 km, que el triatleta tenía que realizar. La velocidad de carrera resulto estar íntimamente ligada al nivel deportivo del triatleta. Del mismo modo, 3 de los 4 grupos analizados presentaron valores inferiores a 3 minutos 30 segundos por kilometro recorrido, poniendo de manifiesto el altísimo nivel de los sujetos analizados. Del mismo modo parece que las chicos consiguen una mayor velocidad gracias a una mayor longitud de ciclo en relación a las chicas, ya que estas muestran valores mayores en cuanto a frecuencia de zancada. La frecuencia de zancada presento los valores más altos en la primera vuelta en todos los deportistas analizados. Asimismo, los triatletas de nivel internacional y las chicas fueron los que mostraron los mayores valores. La longitud de zancada presento distintas tendencias en función del nivel y el género del deportista. Así pues, en los deportistas internacionales y en los chicos los mayores valores se encontraron en la primera vuelta mientras que la tendencia fue al descenso, siendo probablemente la fatiga acumulada la causante de dicha tendencia. En cambio, aquellos deportistas de nivel nacional y las chicas mostraron valores mayores en la segunda vuelta que en la primera, evidenciando que además de la fatiga, el ciclismo previo tiene una incidencia directa sobre su rendimiento. Los tiempos de vuelo permanecieron constantes durante toda la carrera, encontrando cierta evolución en los tiempos de apoyo, la cual provoca una modificación en los porcentajes relativos en los tiempos de vuelo. Los tiempos de apoyo más bajos se encontraron en la primera vuelta. Del mismo modo, los deportistas de nivel internacional y los chicos mostraron valores inferiores. También, estos grupos fueron más constantes en sus valores a lo largo de las vueltas. Por el contrario, se encontraron tendencias al aumento en los triatletas de nivel nacional y en las chicas, los cuales no fueron capaces de mantener el mismo rendimiento debido seguramente a su menor nivel deportivo. La oscilación vertical de la cadera se mostro constante en los triatletas de mayor nivel, encontrándose tendencias al aumento en los de menor nivel. Del mismo modo, los valores más altos correspondieron a las chicas y a los deportistas de nivel nacional. La distancia de la cadera al apoyo permaneció constante a lo largo de las vueltas en todos los grupos, obteniéndose valores mayores en los triatletas de nivel internacional y en los chicos. El ángulo de la rodilla apoyada en el momento del despegue no mostro una tendencia clara. Los deportistas de nivel internacional y los chicos presentaron los valores más bajos. El ángulo de la rodilla libre en el momento del despegue mostro una correlación muy alta con la velocidad de carrera. Del mismo modo, los ángulos más pequeños se encontraron en los triatletas internacionales y en los chicos, debido seguramente a los mayores valores de velocidad registrados por ambos grupos. Los ángulos de los tobillos no mostraron ninguna tendencia clara durante la competición analizada. Los cuatro grupos de población presentaron valores similares, por lo que parece que no representan una variable que pueda incidir sobre el rendimiento biomecánica del triatleta. Los resultados obtenidos en el presente estudio de investigación avalan la utilización de la fotogrametría-video en 2d para el análisis de la técnica de carrera durante la competición en triatlón. Su aplicación en una competición de máximo nivel internacional ha posibilitado conocer el perfil técnico que presentan los triatletas a lo largo del segmento de carrera a pie. Del mismo modo, se ha podido demostrar como los estudios realizados en laboratorio no reflejan la realidad competitiva de un triatlón de máximo nivel. The aim of this research was to determine the running technique profile during a triathlon competition from a biomechanical perspective. Also, to analyze the triathlete gender’s and level of performance’s influence on this profile in competition. An accurate (internal validity) and reliable methodology with a high external validity (ecological) had to be developed to get those aims in competition. Sixty-four triathletes were analyzed. 32 (16 males, 16 females) took part in the Madrid 2008 Triathlon World Cup and 32 (16 males and 16 females) took part in the Spanish Triathlon National Championships. The biomechanical analyses were carried out by a photogrammetric system that allow to calculate the landmarks coordinates (x,y) with a 1.66% error in x axis, and a 2.10% error in y axis. The frames were obtained with a camera situated perpendicular to the triathletes’ trajectory, filming the saggittal plane. DLT based algorithms (Abdel-Aziz & Karara, 1971) were used to calculate the real coordinates from the digitalized ones and the final variables afterwards. The biomechanical analisys itself was performed in four different moments during the competition, according to each 2.5 km lap the triathletes had to do. Running speed was highly related to performance level. Also, 3 of the 4 analyzed groups showed speed values under the 3 minutes and 30 seconds per kilometer. It demonstrated the very high performance level of the analized triathletes. Furthermore, it seems that men get higher speeds because their longer stride length, while women shows higher stride frequency values. The highest stride frequency values were found in the first lap. Women and the international level triathletes showed the highest values. Stride length showed different tendencies according to the gender and level of performance. Men and international level triathletes showed the highest level in the first lap and a decreasing tendency after that. The accumulated fatigue was probably the reason of this tendency. On the other hand, higher values than in first lap were found in the second one in women and national level triathletes. It demonstrated the previous cycling can affect to those groups in terms of biomechanics. Flight times remained constant during the running part, while the contact times showed an increasing tendency that caused a variation in flight times percents. The lowest contact times were found in the first lap and in men and international triathletes’ values. Also, these two groups were more consistent during the whole running. On the other hand, increasing tendencies were found in women and national level triathletes, who were not able to maintain the same values probably due to their lower level of performance. Higher level triathletes showed more consistent hip vertical oscillation values than lower level triathletes, who presented increasing tendencies. The highest values were found in women and national level triathletes. The horizontal distance hip-toe cap remained constant among the laps in all the groups. Men and international level triathletes showed the highest values. The support knee angle at toe-off did not show a clear tendency. The lowest values were found in men and international level triathletes. A high correlation was found between the non-support knee angle and the running speed. Furthermore, men and international level triathletes showed the smallest values, due to the higher velocities reached by these two groups. Ankles angles did not show any tendency during the running part. Similar values were found in the four analyzed groups, so this variable does not seem to represent an important one within the triathlete’s performance. The results obtained in the present research support the use of the bidimensional photogrammetric video-system to analyze the running technique during a triathlon competition. Its application in international triathlon meetings has allowed determining the triathletes’ technique profile during the running part. Also, it has been demonstrated the laboratory-based studies does not reproduce a top-level competition.