Formation of bright solitons and soliton trains in a fermion-fermion mixture by modulational instability

We employ a time- dependent mean- field- hydrodynamic model to study the generation of bright solitons in a degenerate fermion - fermion mixture in a cigar- shaped geometry using variational and numerical methods. Due to a strong Pauli- blocking repulsion among identical spin- polarized fermions at short distances there cannot be bright solitons for repulsive interspecies interactions. Employing a linear stability analysis we demonstrate the formation of stable solitons due to modulational instability of a constant-amplitude solution of the model equations for a sufficiently attractive interspecies interaction. We perform a numerical stability analysis of these solitons and also demonstrate the formation of soliton trains by jumping the effective interspecies interaction from repulsive to attractive. These fermionic solitons can be formed and studied in laboratory with present technology.

Phase-Locked loops lock-in range in Frequency Modulated-Atomic Force Microscope nonlinear control system

Since the mid 1980s the Atomic Force Microscope is one the most powerful tools to perform surface investigation, and since 1995 Non-Contact AFM achieved true atomic resolution. The Frequency-Modulated Atomic Force Microscope (FM-AFM) operates in the dynamic mode, which means that the control system of the FM-AFM must force the micro-cantilever to oscillate with constant amplitude and frequency. However, tip-sample interaction forces cause modulations in the microcantilever motion. A Phase-Locked loop (PLL) is used to demodulate the tip-sample interaction forces from the microcantilever motion. The demodulated signal is used as the feedback signal to the control system, and to generate both topographic and dissipation images. As a consequence, a proper design of the PLL is vital to the FM-AFM performance. In this work, using bifurcation analysis, the lock-in range of the PLL is determined as a function of the frequency shift (Q) of the microcantilever and of the other design parameters, providing a technique to properly design the PLL in the FM-AFM system. (C) 2011 Elsevier B.V. All rights reserved.

Fatigue apparatus for geometrically complex non-standardized specimens

Standard Test Methods (e.g. ASTM, DIN) for materials characterization in general, and for fatigue in particular, do not contemplate specimens with complex geometries, as well as the combination of axial and in-plane bending loads in their methodologies. The present study refers to some patents and the new configuration or configurations of specimens (non-standardized by the status quo of test methods) and a device developed to induce axial and bending combined forces resultants from axial loads applied by any one test equipment (dynamic or monotonic) which possesses such limitation, towards obtaining more realistic results on the fatigue behavior, or even basic mechanical properties, from geometrically complex structures. Motivated by a specific and geometrically complex aeronautic structure (motor-cradle), non-standardized welded tubular specimens made from AISI 4130 steel were fatigue-tested at room temperature, by using a constant amplitude sinusoidal load of 20 Hz frequency, load ratio R = 0.1 with and without the above referred auxiliary fatigue apparatus. The results showed the fatigue apparatus was efficient for introducing higher stress concentration factor at the welded specimen joints, consequently reducing the fatigue strength when compared to other conditions. From the obtained results it is possible to infer that with small modifications the proposed apparatus will be capable to test a great variety of specimen configurations such as: squared tubes and plates with welded or melted junctions, as well as other materials such as aluminum, titanium, composites, polymeric, plastics, etc. © 2009 Bentham Science Publishers Ltd.

Modeling the growth of LT and TL-oriented fatigue cracks in longitudinally and transversely pre-strained Al 2524-T3 alloy

The aluminum alloy 2524 (Al-Cu-Mg) was developed during the 90s mainly to be employed in aircraft fuselage panels, replacing the standard Al 2024. In the present analysis the fatigue crack growth (FCG) behavior of 2524-T3 was investigated, regarding the influence of three parameters: load ratio, pre strain and crack plane orientation of the material. The pre strain of aluminum alloys is usually performed in order to obtain a more homogeneous precipitates distribution, accompanied by an increase in the yield strength. In this work, it was evaluated the resistance of Al 2524-T3 sheet samples to the fatigue crack growth, having L-T and T-L crack orientations. FCG tests were performed under constant amplitude loading at three distinct positive load ratios. The three material conditions were tested: as received(AR), pre strained longitudinally (SL) and transversally (ST) in relation to rolling direction. In order to describe FCG behavior, two-parameter kinetic equations were compared: a Paris-type potential model and a new exponential equation introduced in a previous work conducted by our research group. It was observed that the exponential model, which takes into account the deviations from linearity presented by da/dN versus AK data, describes more adequately the FCG behavior of Al 224-T3 in relation to load ratio, pre strain effects and crack plane orientation. © 2011 Published by Elsevier Ltd.

Fatigue Behavior of Weld Repaired AISI 4130 Aeronautic Steel Used in Critical Flight Safety Structures

Since the 1950s, fatigue is the most important project and operational consideration for both civil and military aircrafts. For some aircraft models the most loaded component is one that supports the motor: the Motor Cradle. Because they are considered critical to the flight safety the aeronautic standards are extremely rigorous in manufacturing them by imposing a zero index of defects on the final weld quality (Safe Life), which is 100% inspected by Non-Destructive Testing/NDT. This study has as objective to evaluate the effects of up to four successive TIG welding repairs on the axial fatigue strength of an AISI 4130 steel. Tests were conducted on hot-rolled steel plate specimens, 0.89 mm thick, with load ratio R = 0.1, constant amplitude, at 20 Hz frequency and in room temperature, in accordance with ASTM E466 Standard. The results were related to microhardness and microstructural and geometric changes resulting from welding cycles.

Estudo do efeito do processo de shot peening na taxa de propagação de trinca por fadiga na liga aeronáutica 2024 - T3

Pós-graduação em Engenharia Mecânica - FEG

Describing fatigue crack growth and load ratio effects in Al 2524 T3 alloy with an enhanced exponential model

The fatigue crack behavior in metals and alloys under constant amplitude test conditions is usually described by relationships between the crack growth rate da/dN and the stress intensity factor range Delta K. In the present work, an enhanced two-parameter exponential equation of fatigue crack growth was introduced in order to describe sub-critical crack propagation behavior of Al 2524-T3 alloy, commonly used in aircraft engineering applications. It was demonstrated that besides adequately correlating the load ratio effects, the exponential model also accounts for the slight deviations from linearity shown by the experimental curves. A comparison with Elber, Kujawski and "Unified Approach" models allowed for verifying the better performance, when confronted to the other tested models, presented by the exponential model. (C) 2012 Elsevier Ltd. All rights reserved.

Phase-Locked loops lock-in range in Frequency Modulated-Atomic Force Microscope nonlinear control system

Since the mid 1980s the Atomic Force Microscope is one the most powerful tools to perform surface investigation, and since 1995 Non-Contact AFM achieved true atomic resolution. The Frequency-Modulated Atomic Force Microscope (FM-AFM) operates in the dynamic mode, which means that the control system of the FM-AFM must force the micro-cantilever to oscillate with constant amplitude and frequency. However, tip-sample interaction forces cause modulations in the microcantilever motion. A Phase-Locked loop (PLL) is used to demodulate the tip-sample interaction forces from the microcantilever motion. The demodulated signal is used as the feedback signal to the control system, and to generate both topographic and dissipation images. As a consequence, a proper design of the PLL is vital to the FM-AFM performance. In this work, using bifurcation analysis, the lock-in range of the PLL is determined as a function of the frequency shift (Q) of the microcantilever and of the other design parameters, providing a technique to properly design the PLL in the FM-AFM system. (C) 2011 Elsevier B.V. All rights reserved.

Vibrations, Posture, and the Stabilization of Gaze: An Experimental Study on Impedance Control

Vibrations, Posture, and the Stabilization of Gaze: An Experimental Study on Impedance Control R. KREDEL, A. GRIMM & E.-J. HOSSNER University of Bern, Switzerland Introduction Franklin and Wolpert (2011) identify impedance control, i.e., the competence to resist changes in position, velocity or acceleration caused by environmental disturbances, as one of five computational mechanisms which allow for skilled and fluent sen-sorimotor behavior. Accordingly, impedance control is of particular interest in situa-tions in which the motor task exhibits unpredictable components as it is the case in downhill biking or downhill skiing. In an experimental study, the question is asked whether impedance control, beyond its benefits for motor control, also helps to stabi-lize gaze what, in turn, may be essential for maintaining other control mechanisms (e.g., the internal modeling of future states) in an optimal range. Method In a 3x2x4 within-subject ANOVA design, 72 participants conducted three tests on visual acuity and contrast (Landolt / Grating and Vernier) in two different postures (standing vs. squat) on a platform vibrating at four different frequencies (ZEPTOR; 0 Hz, 4 Hz, 8 Hz, 12 Hz; no random noise; constant amplitude) in a counterbalanced or-der with 1-minute breaks in-between. In addition, perceived exertion (Borg) was rated by participants after each condition. Results For Landolt and Grating, significant main effects for posture and frequency are re-vealed, representing lower acuity/contrast thresholds for standing and for higher fre-quencies in general, as well as a significant interaction (p < .05), standing for in-creasing posture differences with increasing frequencies. Overall, performance could be maintained at the 0 Hz/standing level up to a frequency of 8 Hz, if bending of the knees was allowed. The fact that this result is not only due to exertion is proved by the Borg ratings showing significant main effects only, i.e., higher exertion scores for standing and for higher frequencies, but no significant interaction (p > .40). The same pattern, although not significant, is revealed for the Vernier test. Discussion Apparently, postures improving impedance control not only turn out to help to resist disturbances but also assist in stabilizing gaze in spite of these perturbations. Con-sequently, studying the interaction of these control mechanisms in complex unpre-dictable environments seems to be a fruitful field of research for the future. References Franklin, D. W., & Wolpert, D. M. (2011). Computational mechanisms of sensorimotor control. Neuron, 72, 425-442.

Análisis del comportamiento a fatiga de uniones adhesivas de acero recubierto

Los adhesivos se conocen y han sido utilizados en multitud de aplicaciones a lo lago de la historia. En la actualidad, la tecnología de la adhesión como método de unión de materiales estructurales está en pleno crecimiento. Los avances científicos han permitido comprender mejor los fenómenos de adhesión, así como, mejorar y desarrollar nuevas formulaciones poliméricas que incrementan el rango de aplicaciones de los adhesivos. Por otro lado, el desarrollo de nuevos materiales y la necesidad de aligerar peso, especialmente en el sector transporte, hace que las uniones adhesivas se introduzcan en aplicaciones hasta ahora reservadas a otros sistemas de unión como la soldadura o las uniones mecánicas, ofreciendo rendimientos similares y, en ocasiones, superiores a los aportados por estas. Las uniones adhesivas ofrecen numerosas ventajas frente a otros sistemas de unión. En la industria aeronáutica y en automoción, las uniones adhesivas logran una reducción en el número de componentes (tales como los tornillos, remaches, abrazaderas) consiguiendo como consecuencia diseños más ligeros y una disminución de los costes de manipulación y almacenamiento, así como una aceleración de los procesos de ensamblaje, y como consecuencia, un aumento de los procesos de producción. En el sector de la construcción y en la fabricación de equipos industriales, se busca la capacidad para soportar la expansión y contracción térmica. Por lo tanto, se usan las uniones adhesivas para evitar producir la distorsión del sustrato al no ser necesario el calentamiento ni la deformación de las piezas cuando se someten a un calentamiento elevado y muy localizado, como en el caso de la soldadura, o cuando se someten a esfuerzos mecánicos localizados, en el caso de montajes remachados. En la industria naval, se están desarrollando técnicas de reparación basadas en la unión adhesiva para distribuir de forma más uniforme y homogénea las tensiones con el objetivo de mejorar el comportamiento frente a fatiga y evitar los problemas asociados a las técnicas de reparación habituales de corte y soldadura. Las uniones adhesivas al no requerir importantes aportes de calor como la soldadura, no producen modificaciones microestructurales indeseables como sucede en la zona fundida o en la zona afectada térmicamente de las uniones soldadas, ni deteriora los recubrimientos protectores de metales de bajo punto de fusión o de naturaleza orgánica. Sin embargo, las uniones adhesivas presentan una desventaja que dificulta su aplicación, se trata de su durabilidad a largo plazo. La primera causa de rotura de los materiales es la rotura por fatiga. Este proceso de fallo es la causa del 85% de las roturas de los materiales estructurales en servicio. La rotura por fatiga se produce cuando se somete al material a la acción de cargas que varían cíclicamente o a vibraciones durante un tiempo prolongado. Las uniones y estructuras sometidas a fatiga pueden fallar a niveles de carga por debajo del límite de resistencia estática del material. La rotura por fatiga en las uniones adhesivas no se produce por un proceso de iniciación y propagación de grieta de forma estable, el proceso de fatiga va debilitando poco a poco la unión hasta que llega un momento que provoca una rotura de forma rápida. Underhill explica este mecanismo como un proceso de daño irreversible de los enlaces más débiles en determinados puntos de la unión. Cuando se ha producido el deterioro de estas zonas más débiles, su área se va incrementando hasta que llega un momento en que la zona dañada es tan amplia que se produce el fallo completo de la unión. En ensayos de crecimiento de grieta realizados sobre probetas preagrietadas en viga con doble voladizo (DCB), Dessureault identifica los procesos de iniciación y crecimiento de grietas en muestras unidas con adhesivo epoxi como una acumulación de microfisuras en la zona próxima al fondo de grieta que, luego, van coalesciendo para configurar la grieta principal. Lo que supone, igualmente, un proceso de daño del adhesivo en la zona de mayor concentración de tensiones que, posteriormente, conduce al fallo de la unión. La presente tesis surge con el propósito de aumentar los conocimientos existentes sobre el comportamiento a fatiga de las uniones adhesivas y especialmente las realizadas con dos tipos de adhesivos estructurales aplicados en aceros con diferentes acabados superficiales. El estudio incluye la obtención de las curvas de tensión frente al número de ciclos hasta el fallo del componente, curvas SN o curvas de Wöhler, que permitirán realizar una estimación de la resistencia a la fatiga de un determinado material o estructura. Los ensayos de fatiga realizados mediante ciclos predeterminados de carga sinusoidales, de amplitud y frecuencia constantes, han permitido caracterizar el comportamiento a la fatiga por el número de ciclos hasta la rotura, siendo el límite de fatiga el valor al que tiende la tensión cuando el número de ciclos es muy grande. En algunos materiales, la fatiga no tiende a un valor límite sino que decrece de forma constante a medida que aumenta el número de ciclos. Para estas situaciones, se ha definido la resistencia a la fatiga (o límite de resistencia) por la tensión en que se produce la rotura para un número de ciclos predeterminado. Todos estos aspectos permitirán un mejor diseño de las uniones y las condiciones de trabajo de los adhesivos con el fin de lograr que la resistencia a fatiga de la unión sea mucho más duradera y el comportamiento total de la unión sea mucho mejor, contribuyendo al crecimiento de la utilización de las uniones adhesivas respecto a otras técnicas. ABSTRACT Adhesives are well-known and have been used in many applications throughout history. At present, adhesion bonding technology of structural materials is experiencing an important growth. Scientific advances have enabled a better understanding of the phenomena of adhesion, as well as to improve and develop new polymeric formulations that increase the range of applications. On the other hand, the development of new materials and the need to save weight, especially in the transport sector, have promote the use of adhesive bonding in many applications previously reserved for other joining technologies such as welded or mechanical joints, presenting similar or even higher performances. Adhesive bonding offers many advantages over other joining methods. For example, in the aeronautic industry and in the automation sector, adhesive bonding allows a reduction in the number of components (such as bolts, rivets, clamps) and as consequence, resulting in lighter designs and a decrease in handling and storage costs, as well as faster assembly processes and an improvement in the production processes. In the construction sector and in the industrial equipment manufacturing, the ability to withstand thermal expansion and contraction is required. Therefore, adhesion bonding technology is used to avoid any distortion of the substrate since this technology does not require heating nor the deformation of the pieces when these are exposed to very high and localized heating, as in welding, or when are subjected to localized mechanical stresses in the case of riveted joints. In the naval industry, repair techniques based in the adhesive bonding are being developed in order to distribute stresses more uniform and homogeneously in order to improve the performance against fatigue and to avoid the problems associated with standard repair techniques as cutting and welding. Adhesive bonding does not require the use of high temperatures and as consequence they do not produce undesirable microstructural changes, as it can be observed in molten zones or in heat-affected zones in the case of welding, neither is there damage of the protective coating of metals with low melting points or polymeric films. However, adhesive bonding presents a disadvantage that limits its application, the low longterm durability. The most common cause of fractures of materials is fatigue fracture. This failure process is the cause of 85% of the fracture of structural materials in service. Fatigue failure occurs when the materials are subjected to the action of cyclic loads or vibrations for a long period of time. The joints and structures subjected to fatigue can fail at stress values below the static strength of the material. Fatigue failure do not occurs by a static and homogeneous process of initiation and propagation of crack. The fatigue process gradually weakens the bond until the moment in which the fracture occurs very rapidly. Underhill explains this mechanism as a process of irreversible damage of the weakest links at certain points of the bonding. When the deterioration in these weaker zones occurs, their area increase until the damage zone is so extensive that the full failure of the joint occurs. During the crack growth tests performed on precracked double-cantilever beam specimen, (DCB), Dessureault identified the processes of crack initiation and growth in samples bonded with epoxy adhesive as a process of accumulation of microcracks on the zone near the crack bottom, then, they coalesced to configure the main crack. This is a damage process of the adhesive in the zone of high stress concentration that leads to failure of the bond. This thesis aims to further the understanding of the fatigue behavior of the adhesive bonding, primarily those based on two different types of structural adhesives used on carbon-steel with different surface treatments. This memory includes the analysis of the SN or Wöhler curves (stress vs. number of cycles curves up to the failure), allowing to carry out an estimation of the fatigue strength of a specific material or structure. The fatigue tests carried out by means of predetermined cycles of sinusoidal loads, with a constant amplitude and frequency, allow the characterisation of the fatigue behaviour. For some materials, there is a maximum stress amplitude below which the material never fails for any number of cycles, known as fatigue limit. In the other hand, for other materials, the fatigue does not tend toward a limit value but decreases constantly as the number of cycles increases. For these situations, the fatigue strength is defined by the stress at which the fracture occurs for a predetermined number of cycles. All these aspects will enable a better joint design and service conditions of adhesives in order to get more durable joints from the fatigue failure point of view and in this way contribute to increase the use of adhesive bonding over other joint techniques.

Fatiga en CFRP: Caracterización y Método Óptico para la Estimación del Daño

El desarrollo de nuevas estructuras aeroespaciales optimizadas, utilizan materiales compuestos, para los componentes críticos y subsistemas, principalmente polímeros reforzados con fibra de carbono (CFRP). Un conocimiento profundo del estado de daño por fatiga de estructuras de CFRP avanzado, es esencial para predecir la vida residual y optimizar los intervalos de inspección estructural, reparaciones y/o sustitución de componentes. Las técnicas actuales se basan principalmente en la medición de cargas estructurales a lo largo de la vida útil de la estructura mediante galgas extensométricas eléctricas. Con esos datos, se estima la vida a fatiga utilizando modelos de acumulación de daño. En la presente tesis, se evalúa la metodología convencional para la estimación de la vida a fatiga de un CFRP aeronáutico. Esta metodología está basada en la regla de acumulación de daño lineal de Palmgren-Miner, y es aplicada para determinar la vida a fatiga de estructuras sometidas a cargas de amplitud variable. Se ha realizado una campaña de ensayos con cargas de amplitud constante para caracterizar un CFRP aeronáutico a fatiga, obteniendo las curvas clásicas S-N, en diferentes relaciones de esfuerzo. Se determinaron los diagramas de vida constante, (CLD), también conocidos como diagramas de Goodman, utilizando redes neuronales artificiales debido a la ausencia de modelos coherentes para materiales compuestos. Se ha caracterizado la degradación de la rigidez debido al daño por fatiga. Se ha ensayado un segundo grupo de probetas con secuencias estandarizadas de cargas de amplitud variable, para obtener la vida a fatiga y la degradación de rigidez en condiciones realistas. Las cargas aplicadas son representativas de misiones de aviones de combate (Falstaff), y de aviones de transporte (Twist). La vida a fatiga de las probetas cicladas con cargas de amplitud variable, se comparó con el índice de daño teórico calculado en base a la regla de acumulación de daño lineal convencional. Los resultados obtenidos muestran predicciones no conservativas. Esta tesis también presenta el estudio y desarrollo, de una nueva técnica de no contacto para evaluar el estado de daño por fatiga de estructuras de CFRP por medio de cambios de los parámetros de rugosidad. La rugosidad superficial se puede medir fácilmente en campo con métodos sin contacto, mediante técnicas ópticas tales como speckle y perfilómetros ópticos. En el presente estudio, se han medido parámetros de rugosidad superficial, y el factor de irregularidad de la superficie, a lo largo de la vida de las probetas cicladas con cargas de amplitud constante y variable, Se ha obtenido una buena tendencia de ajuste al correlacionar la magnitud de la rugosidad y el factor de irregularidad de la superficie con la degradación de la rigidez de las probetas fatigadas. Estos resultados sugieren que los cambios en la rugosidad superficial medida en zonas estratégicas de componentes y estructuras hechas de CFRP, podrían ser indicativas del nivel de daño interno debido a cargas de fatiga. Los resultados también sugieren que el método es independiente del tipo de carga de fatiga que ha causado el daño. Esto último hace que esta técnica de medición sea aplicable como inspección para una amplia gama de estructuras de materiales compuestos, desde tanques presurizados con cargas de amplitud constante, estructuras aeronáuticas como alas y colas de aeronaves cicladas con cargas de amplitud variable, hasta aplicaciones industriales como automoción, entre otros. ABSTRACT New optimized aerospace structures use composite materials, mainly carbon fiber reinforced polymer composite (CFRP), for critical components and subsystems. A strong knowledge of the fatigue state of highly advanced (CFRP) structures is essential to predict the residual life and optimize intervals of structural inspection, repairs, and/or replacements. Current techniques are based mostly on measurement of structural loads throughout the service life by electric strain gauge sensors. These sensors are affected by extreme environmental conditions and by fatigue loads in such a way that the sensors and their systems require exhaustive maintenance throughout system life. In the present thesis, the conventional methodology based on linear damage accumulation rules, applied to determine the fatigue life of structures subjected to variable amplitude loads was evaluated for an aeronautical CFRP. A test program with constant amplitude loads has been performed to obtain the classical S-N curves at different stress ratios. Constant life diagrams, CLDs, where determined by means of Artificial Neural Networks due to the absence of consistent models for composites. The stiffness degradation due to fatigue damage has been characterized for coupons under cyclic tensile loads. A second group of coupons have been tested until failure with a standardized sequence of variable amplitude loads, representative of missions for combat aircraft (Falstaff), and representative of commercial flights (Twist), to obtain the fatigue life and the stiffness degradation under realistic conditions. The fatigue life of the coupons cycled with variable amplitude loads were compared to the theoretical damage index calculated based on the conventional linear damage accumulation rule. The obtained results show non-conservative predictions. This thesis also presents the evaluation of a new non-contact technique to evaluate the fatigue damage state of CFRP structures by means of measuring roughness parameters to evaluate changes in the surface topography. Surface roughness can be measured easily on field with non-contact methods by optical techniques such as speckle and optical perfilometers. In the present study, surface roughness parameters, and the surface irregularity factor, have been measured along the life of the coupons cycled with constant and variable amplitude loads of different magnitude. A good agreement has been obtained when correlating the magnitude of the roughness and the surface irregularity factor with the stiffness degradation. These results suggest that the changes on the surface roughness measured in strategic zones of components and structures made of CFRP, could be indicative of the level of internal damage due to fatigue loads. The results also suggest that the method is independent of the type of fatigue load that have caused the damage. It makes this measurement technique applicable for a wide range of inspections of composite materials structures, from pressurized tanks with constant amplitude loads, to variable amplitude loaded aeronautical structures like wings and empennages, up to automotive and other industrial applications.

Non contact inspection of the fatigue damage state of carbon fiber reinforced polymer by optical surface roughness measurements

This work presents the evaluation of a new non-contact technique to assess the fatigue damage state of CFRP structures by measuring surface roughness parameters. Surface roughness and stiffness degradation have been measured in CFRP coupons cycled with constant amplitude loads, and a Pearson?s correlation of 0.79 was obtained between both variables. Results suggest that changes on the surface roughness measured in strategic zones of components made of the evaluated CFRP, could be indicative of the level of damage due to fatigue loads. This methodology could be useful for other FRP due to similarities in the fatigue damage process.

Optical sensing of the fatigue damage state of CFRP under realistic aeronautical load sequences

We present an optical sensing methodology to estimate the fatigue damage state of structures made of carbon fiber reinforced polymer (CFRP), by measuring variations on the surface roughness. Variable amplitude loads (VAL), which represent realistic loads during aeronautical missions of fighter aircraft (FALSTAFF) have been applied to coupons until failure. Stiffness degradation and surface roughness variations have been measured during the life of the coupons obtaining a Pearson correlation of 0.75 between both variables. The data were compared with a previous study for Constant Amplitude Load (CAL) obtaining similar results. Conclusions suggest that the surface roughness measured in strategic zones is a useful technique for structural health monitoring of CFRP structures, and that it is independent of the type of load applied. Surface roughness can be measured in the field by optical techniques such as speckle, confocal perfilometers and interferometry, among others.

Reciprocal electromechanical properties of rat prestin: The motor molecule from rat outer hair cells

Cochlear outer hair cells (OHCs) are responsible for the exquisite sensitivity, dynamic range, and frequency-resolving capacity of the mammalian hearing organ. These unique cells respond to an electrical stimulus with a cycle-by-cycle change in cell length that is mediated by molecular motors in the cells' basolateral membrane. Recent work identified prestin, a protein with similarity to pendrin-related anion transporters, as the OHC motor molecule. Here we show that heterologously expressed prestin from rat OHCs (rprestin) exhibits reciprocal electromechanical properties as known for the OHC motor protein. Upon electrical stimulation in the microchamber configuration, rprestin generates mechanical force with constant amplitude and phase up to a stimulus frequency of at least 20 kHz. Mechanical stimulation of rprestin in excised outside-out patches shifts the voltage dependence of the nonlinear capacitance characterizing the electrical properties of the molecule. The results indicate that rprestin is a molecular motor that displays reciprocal electromechanical properties over the entire frequency range relevant for mammalian hearing.

Sviluppo e applicazione di nuovi criteri per la verifica a fatica multiassiale di componenti strutturali in leghe di acciaio e alluminio

La presente Tesi ha per oggetto lo sviluppo e la validazione di nuovi criteri per la verifica a fatica multiassiale di componenti strutturali metallici . In particolare, i nuovi criteri formulati risultano applicabili a componenti metallici, soggetti ad un’ampia gamma di configurazioni di carico: carichi multiassiali variabili nel tempo, in modo ciclico e random, per alto e basso/medio numero di cicli di carico. Tali criteri costituiscono un utile strumento nell’ambito della valutazione della resistenza/vita a fatica di elementi strutturali metallici, essendo di semplice implementazione, e richiedendo tempi di calcolo piuttosto modesti. Nel primo Capitolo vengono presentate le problematiche relative alla fatica multiassiale, introducendo alcuni aspetti teorici utili a descrivere il meccanismo di danneggiamento a fatica (propagazione della fessura e frattura finale) di componenti strutturali metallici soggetti a carichi variabili nel tempo. Vengono poi presentati i diversi approcci disponibili in letteratura per la verifica a fatica multiassiale di tali componenti, con particolare attenzione all'approccio del piano critico. Infine, vengono definite le grandezze ingegneristiche correlate al piano critico, utilizzate nella progettazione a fatica in presenza di carichi multiassiali ciclici per alto e basso/medio numero di cicli di carico. Il secondo Capitolo è dedicato allo sviluppo di un nuovo criterio per la valutazione della resistenza a fatica di elementi strutturali metallici soggetti a carichi multiassiali ciclici e alto numero di cicli. Il criterio risulta basato sull'approccio del piano critico ed è formulato in termini di tensioni. Lo sviluppo del criterio viene affrontato intervenendo in modo significativo su una precedente formulazione proposta da Carpinteri e collaboratori nel 2011. In particolare, il primo intervento riguarda la determinazione della giacitura del piano critico: nuove espressioni dell'angolo che lega la giacitura del piano critico a quella del piano di frattura vengono implementate nell'algoritmo del criterio. Il secondo intervento è relativo alla definizione dell'ampiezza della tensione tangenziale e un nuovo metodo, noto come Prismatic Hull (PH) method (di Araújo e collaboratori), viene implementato nell'algoritmo. L'affidabilità del criterio viene poi verificata impiegando numerosi dati di prove sperimentali disponibili in letteratura. Nel terzo Capitolo viene proposto un criterio di nuova formulazione per la valutazione della vita a fatica di elementi strutturali metallici soggetti a carichi multiassiali ciclici e basso/medio numero di cicli. Il criterio risulta basato sull'approccio del piano critico, ed è formulato in termini di deformazioni. In particolare, la formulazione proposta trae spunto, come impostazione generale, dal criterio di fatica multiassiale in regime di alto numero di cicli discusso nel secondo Capitolo. Poiché in presenza di deformazioni plastiche significative (come quelle caratterizzanti la fatica per basso/medio numero di cicli di carico) è necessario conoscere il valore del coefficiente efficace di Poisson del materiale, vengono impiegate tre differenti strategie. In particolare, tale coefficiente viene calcolato sia per via analitica, che per via numerica, che impiegando un valore costante frequentemente adottato in letteratura. Successivamente, per validarne l'affidabilità vengono impiegati numerosi dati di prove sperimentali disponibili in letteratura; i risultati numerici sono ottenuti al variare del valore del coefficiente efficace di Poisson. Inoltre, al fine di considerare i significativi gradienti tensionali che si verificano in presenza di discontinuità geometriche, come gli intagli, il criterio viene anche esteso al caso dei componenti strutturali intagliati. Il criterio, riformulato implementando il concetto del volume di controllo proposto da Lazzarin e collaboratori, viene utilizzato per stimare la vita a fatica di provini con un severo intaglio a V, realizzati in lega di titanio grado 5. Il quarto Capitolo è rivolto allo sviluppo di un nuovo criterio per la valutazione del danno a fatica di elementi strutturali metallici soggetti a carichi multiassiali random e alto numero di cicli. Il criterio risulta basato sull'approccio del piano critico ed è formulato nel dominio della frequenza. Lo sviluppo del criterio viene affrontato intervenendo in modo significativo su una precedente formulazione proposta da Carpinteri e collaboratori nel 2014. In particolare, l’intervento riguarda la determinazione della giacitura del piano critico, e nuove espressioni dell'angolo che lega la giacitura del piano critico con quella del piano di frattura vengono implementate nell'algoritmo del criterio. Infine, l’affidabilità del criterio viene verificata impiegando numerosi dati di prove sperimentali disponibili in letteratura.