Atmospheric pollutants in São Paulo state, Brazil and effects on human health – a review

Fundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP)

Dynamic wetting of complex liquids

A simple dependency between contact angle θ and velocity or surface tension has been predicted for the wetting and dewetting behavior of simple liquids. According to the hydrodynamic theory, this dependency was described by Cox and Voinov as θ ∼ Ca^(1/3) (Ca: Capillary number). For more complex liquids like surfactant solutions, this prediction is not directly given.rnHere I present a rotating drum setup for studying wetting/dewetting processes of surfactant solutions on the basis of velocity-dependent contact angle measurements. With this new setup I showed that surfactant solutions do not follow the predicted Cox-Voinov relation, but showed a stronger contact angle dependency on surface tension. All surfactants independent of their charge showed this difference from the prediction so that electrostatic interactions as a reason could be excluded. Instead, I propose the formation of a surface tension gradient close to the three-phase contact line as the main reason for the strong contact angle decrease with increasing surfactant concentration. Surface tension gradients are not only formed locally close to the three-phase contact line, but also globally along the air-liquid interface due to the continuous creation/destruction of the interface by the drum moving out of/into the liquid. By systematically hindering the equilibration routes of the global gradient along the interface and/or through the bulk, I was able to show that the setup geometry is also important for the wetting/dewetting of surfactant solutions. Further, surface properties like roughness or chemical homogeneity of the wetted/dewetted substrate influence the wetting/dewetting behavior of the liquid, i. e. the three-phase contact line is differently pinned on rough/smooth or homogeneous/inhomogeneous surfaces. Altogether I showed that the wetting/dewetting of surfactant solutions did not depend on the surfactant type (anionic, cationic, or non-ionic) but on the surfactant concentration and strength, the setup geometry, and the surface properties.rnSurfactants do not only influence the wetting/dewetting behavior of liquids, but also the impact behavior of drops on free-standing films or solutions. In a further part of this work, I dealt with the stability of the air cushion between drop and film/solution. To allow coalescence between drop and substrate, the air cushion has to vanish. In the presence of surfactants, the vanishing of the air is slowed down due to a change in the boundary condition from slip to no-slip, i. e. coalescence is suppressed or slowed down in the presence of surfactant.

Análisis del acoplamiento vibro-acústico en resonadores de membrana

El presente Trabajo Fin de Máster pretende llevar a cabo el análisis del comportamiento vibratorio de resonadores de membrana, consistentes en un panel delgado y ligero montado a cierta distancia de un elemento constructivo rígido y pesado. Este tipo de sistemas resonantes son empleados habitualmente como absorbentes de media-baja frecuencia en aplicaciones de acondicionamiento acústico de salas. El análisis hará especial hincapié en la influencia del acoplamiento mecánico-acústico entre la placa vibrante (estructura) y el colchón de aire (fluido) encerrado entre la misma y la pared rígida. En primer lugar, realizaremos el análisis modal experimental del resonador objeto de ensayo a partir de las mediciones de su respuesta vibratoria, con el fin de caracterizar su comportamiento en base a sus primeros modos propios acoplados de flexión. El análisis de las señales vibratorias en el dominio de la frecuencia para la identificación de dicho modos se realizará en el entorno de programación MATLAB, haciendo uso de una herramienta propia que implementa los métodos de cálculo y los algoritmos necesarios para tal fin. Asimismo, simularemos el comportamiento del resonador mediante el método de elementos finitos (FEM), utilizando las aplicaciones ANSYS y SYSNOISE, considerando diferentes condiciones frontera en el modelo generado. Los resultados aquí obtenidos serán de utilidad para complementar aquellos obtenidos de forma experimental a la hora de extraer conclusiones prácticas del análisis realizado. SUMMARY. This Master's Thesis intends to carry out the analysis of the vibratory behaviour of resonance absorbers, consisting of a thin and lightweight panel mounted at a distance from a rigid wall. Such systems are commonly used as sound absorption systems for mid-low frequency in room acoustics applications. The analysis will emphasize the influence of mechanical-acoustic coupling between the vibrating plate (structure) and the air cushion (acoustic element) enclosed behind it. First of all, we are performing the experimental modal analysis of the resonance absorber under test from the vibrational response measurements, in order to characterize its behaviour based on its first bending coupled-modes. The analysis of vibration signals in the frequency domain for the identification of such modes will be made in MATLAB programming environment, using a proprietary tool that implements the calculation methods and algorithms needed for this purpose. Furthermore, we are simulating the behaviour of the resonance absorber applying the Finite Element Method (FEM) – using ANSYS and SYSNOISE applications - considering different boundary conditions in the model created. The results from the simulation will be useful to complement those obtained experimentally when drawing practical conclusions from this analysis.

Robust flight stability and control for micro air vehicles.

This chapter presents the real time validation of fixed order robust 112 controller designed for the lateral stabilisation of a micro air vehicle named Sarika2. Digital signal processor (DSP) based onboard computer named flight instrumentation controller (FIC) is designed to operate under automatic or manual mode. FIC gathers data from multitude of sensors and is capable of closed loop control to enable autonomous flight. Fixed order lateral H-2 controller designed with the features such as incorporation of level I flying qualities, gust alleviation and noise rejection is coded on to the FIC. Challenging real time hardware in loop simulation (HILS) is done with dSPACE1104 RTI/RTW. Responses obtained from the HILS are compared with those obtained from the offline simulation. Finally, flight trials are conducted to demonstrate the satisfactory performance of the closed loop system. The generic design methodology developed is applicable to all classes of Mini and Micro air vehicles.

A fractional order proportional integral controller for path following and trajectory tracking of miniature air vehicles

In this paper, a fractional order proportional-integral controller is developed for a miniature air vehicle for rectilinear path following and trajectory tracking. The controller is implemented by constructing a vector field surrounding the path to be followed, which is then used to generate course commands for the miniature air vehicle. The fractional order proportional-integral controller is simulated using the fundamentals of fractional calculus, and the results for this controller are compared with those obtained for a proportional controller and a proportional integral controller. In order to analyze the performance of the controllers, four performance metrics, namely (maximum) overshoot, control effort, settling time and integral of the timed absolute error cost, have been selected. A comparison of the nominal as well as the robust performances of these controllers indicates that the fractional order proportional-integral controller exhibits the best performance in terms of ITAE while showing comparable performances in all other aspects.

Use of calculus of variations to determine the shape of hovering rotors of minimum power and its application to micro air vehicles

In this paper, calculus of variations and combined blade element and momentum theory (BEMT) are used to demonstrate that, in hover, when neither root nor tip losses are considered; the rotor, which minimizes the total power (MPR), generates an induced velocity that varies linearly along the blade span. The angle of attack of every blade element is constant and equal to its optimum value. The traditional ideal twist (ITR) and optimum (OR) rotors are revisited in the context of this variational framework. Two more optimum rotors are obtained considering root and tip losses, the ORL, and the MPRL. A comparison between these five rotors is presented and discussed. The MPR and MPRL present a remarkable saving of power for low values of both thrust coefficient and maximum aerodynamic efficiency. The result obtained can be exploited to improve the aerodynamic behaviour of rotary wing micro air vehicles (MAV). A comparison with experimental results obtained from the literature is presented.