Methodologies for Collision Risk Computation = Metodologías para Cálculo de Riesgo de Colisión

Esta tesis aborda metodologías para el cálculo de riesgo de colisión de satélites. La minimización del riesgo de colisión se debe abordar desde dos puntos de vista distintos. Desde el punto de vista operacional, es necesario filtrar los objetos que pueden presentar un encuentro entre todos los objetos que comparten el espacio con un satélite operacional. Puesto que las órbitas, del objeto operacional y del objeto envuelto en la colisión, no se conocen perfectamente, la geometría del encuentro y el riesgo de colisión deben ser evaluados. De acuerdo con dicha geometría o riesgo, una maniobra evasiva puede ser necesaria para evitar la colisión. Dichas maniobras implican un consumo de combustible que impacta en la capacidad de mantenimiento orbital y por tanto de la visa útil del satélite. Por tanto, el combustible necesario a lo largo de la vida útil de un satélite debe ser estimado en fase de diseño de la misión para una correcta definición de su vida útil, especialmente para satélites orbitando en regímenes orbitales muy poblados. Los dos aspectos, diseño de misión y aspectos operacionales en relación con el riesgo de colisión están abordados en esta tesis y se resumen en la Figura 3. En relación con los aspectos relacionados con el diseño de misión (parte inferior de la figura), es necesario evaluar estadísticamente las características de de la población espacial y las teorías que permiten calcular el número medio de eventos encontrados por una misión y su capacidad de reducir riesgo de colisión. Estos dos aspectos definen los procedimientos más apropiados para reducir el riesgo de colisión en fase operacional. Este aspecto es abordado, comenzando por la teoría descrita en [Sánchez-Ortiz, 2006]T.14 e implementada por el autor de esta tesis en la herramienta ARES [Sánchez-Ortiz, 2004b]T.15 proporcionada por ESA para la evaluación de estrategias de evitación de colisión. Esta teoría es extendida en esta tesis para considerar las características de los datos orbitales disponibles en las fases operacionales de un satélite (sección 4.3.3). Además, esta teoría se ha extendido para considerar riesgo máximo de colisión cuando la incertidumbre de las órbitas de objetos catalogados no es conocida (como se da el caso para los TLE), y en el caso de querer sólo considerar riesgo de colisión catastrófico (sección 4.3.2.3). Dichas mejoras se han incluido en la nueva versión de ARES [Domínguez-González and Sánchez-Ortiz, 2012b]T.12 puesta a disposición a través de [SDUP,2014]R.60. En fase operacional, los catálogos que proporcionan datos orbitales de los objetos espaciales, son procesados rutinariamente, para identificar posibles encuentros que se analizan en base a algoritmos de cálculo de riesgo de colisión para proponer maniobras de evasión. Actualmente existe una única fuente de datos públicos, el catálogo TLE (de sus siglas en inglés, Two Line Elements). Además, el Joint Space Operation Center (JSpOC) Americano proporciona mensajes con alertas de colisión (CSM) cuando el sistema de vigilancia americano identifica un posible encuentro. En función de los datos usados en fase operacional (TLE o CSM), la estrategia de evitación puede ser diferente debido a las características de dicha información. Es preciso conocer las principales características de los datos disponibles (respecto a la precisión de los datos orbitales) para estimar los posibles eventos de colisión encontrados por un satélite a lo largo de su vida útil. En caso de los TLE, cuya precisión orbital no es proporcionada, la información de precisión orbital derivada de un análisis estadístico se puede usar también en el proceso operacional así como en el diseño de la misión. En caso de utilizar CSM como base de las operaciones de evitación de colisiones, se conoce la precisión orbital de los dos objetos involucrados. Estas características se han analizado en detalle, evaluando estadísticamente las características de ambos tipos de datos. Una vez concluido dicho análisis, se ha analizado el impacto de utilizar TLE o CSM en las operaciones del satélite (sección 5.1). Este análisis se ha publicado en una revista especializada [Sánchez-Ortiz, 2015b]T.3. En dicho análisis, se proporcionan recomendaciones para distintas misiones (tamaño del satélite y régimen orbital) en relación con las estrategias de evitación de colisión para reducir el riesgo de colisión de manera significativa. Por ejemplo, en el caso de un satélite en órbita heliosíncrona en régimen orbital LEO, el valor típico del ACPL que se usa de manera extendida es 10-4. Este valor no es adecuado cuando los esquemas de evitación de colisión se realizan sobre datos TLE. En este caso, la capacidad de reducción de riesgo es prácticamente nula (debido a las grandes incertidumbres de los datos TLE) incluso para tiempos cortos de predicción. Para conseguir una reducción significativa del riesgo, sería necesario usar un ACPL en torno a 10-6 o inferior, produciendo unas 10 alarmas al año por satélite (considerando predicciones a un día) o 100 alarmas al año (con predicciones a tres días). Por tanto, la principal conclusión es la falta de idoneidad de los datos TLE para el cálculo de eventos de colisión. Al contrario, usando los datos CSM, debido a su mejor precisión orbital, se puede obtener una reducción significativa del riesgo con ACPL en torno a 10-4 (considerando 3 días de predicción). Incluso 5 días de predicción pueden ser considerados con ACPL en torno a 10-5. Incluso tiempos de predicción más largos se pueden usar (7 días) con reducción del 90% del riesgo y unas 5 alarmas al año (en caso de predicciones de 5 días, el número de maniobras se mantiene en unas 2 al año). La dinámica en GEO es diferente al caso LEO y hace que el crecimiento de las incertidumbres orbitales con el tiempo de propagación sea menor. Por el contrario, las incertidumbres derivadas de la determinación orbital son peores que en LEO por las diferencias en las capacidades de observación de uno y otro régimen orbital. Además, se debe considerar que los tiempos de predicción considerados para LEO pueden no ser apropiados para el caso de un satélite GEO (puesto que tiene un periodo orbital mayor). En este caso usando datos TLE, una reducción significativa del riesgo sólo se consigue con valores pequeños de ACPL, produciendo una alarma por año cuando los eventos de colisión se predicen a un día vista (tiempo muy corto para implementar maniobras de evitación de colisión).Valores más adecuados de ACPL se encuentran entre 5•10-8 y 10-7, muy por debajo de los valores usados en las operaciones actuales de la mayoría de las misiones GEO (de nuevo, no se recomienda en este régimen orbital basar las estrategias de evitación de colisión en TLE). Los datos CSM permiten una reducción de riesgo apropiada con ACPL entre 10-5 y 10-4 con tiempos de predicción cortos y medios (10-5 se recomienda para predicciones a 5 o 7 días). El número de maniobras realizadas sería una en 10 años de misión. Se debe notar que estos cálculos están realizados para un satélite de unos 2 metros de radio. En el futuro, otros sistemas de vigilancia espacial (como el programa SSA de la ESA), proporcionarán catálogos adicionales de objetos espaciales con el objetivo de reducir el riesgo de colisión de los satélites. Para definir dichos sistemas de vigilancia, es necesario identificar las prestaciones del catalogo en función de la reducción de riesgo que se pretende conseguir. Las características del catálogo que afectan principalmente a dicha capacidad son la cobertura (número de objetos incluidos en el catalogo, limitado principalmente por el tamaño mínimo de los objetos en función de las limitaciones de los sensores utilizados) y la precisión de los datos orbitales (derivada de las prestaciones de los sensores en relación con la precisión de las medidas y la capacidad de re-observación de los objetos). El resultado de dicho análisis (sección 5.2) se ha publicado en una revista especializada [Sánchez-Ortiz, 2015a]T.2. Este análisis no estaba inicialmente previsto durante la tesis, y permite mostrar como la teoría descrita en esta tesis, inicialmente definida para facilitar el diseño de misiones (parte superior de la figura 1) se ha extendido y se puede aplicar para otros propósitos como el dimensionado de un sistema de vigilancia espacial (parte inferior de la figura 1). La principal diferencia de los dos análisis se basa en considerar las capacidades de catalogación (precisión y tamaño de objetos observados) como una variable a modificar en el caso de un diseño de un sistema de vigilancia), siendo fijas en el caso de un diseño de misión. En el caso de las salidas generadas en el análisis, todos los aspectos calculados en un análisis estadístico de riesgo de colisión son importantes para diseño de misión (con el objetivo de calcular la estrategia de evitación y la cantidad de combustible a utilizar), mientras que en el caso de un diseño de un sistema de vigilancia, los aspectos más importantes son el número de maniobras y falsas alarmas (fiabilidad del sistema) y la capacidad de reducción de riesgo (efectividad del sistema). Adicionalmente, un sistema de vigilancia espacial debe ser caracterizado por su capacidad de evitar colisiones catastróficas (evitando así in incremento dramático de la población de basura espacial), mientras que el diseño de una misión debe considerar todo tipo de encuentros, puesto que un operador está interesado en evitar tanto las colisiones catastróficas como las letales. Del análisis de las prestaciones (tamaño de objetos a catalogar y precisión orbital) requeridas a un sistema de vigilancia espacial se concluye que ambos aspectos han de ser fijados de manera diferente para los distintos regímenes orbitales. En el caso de LEO se hace necesario observar objetos de hasta 5cm de radio, mientras que en GEO se rebaja este requisito hasta los 100 cm para cubrir las colisiones catastróficas. La razón principal para esta diferencia viene de las diferentes velocidades relativas entre los objetos en ambos regímenes orbitales. En relación con la precisión orbital, ésta ha de ser muy buena en LEO para poder reducir el número de falsas alarmas, mientras que en regímenes orbitales más altos se pueden considerar precisiones medias. En relación con los aspectos operaciones de la determinación de riesgo de colisión, existen varios algoritmos de cálculo de riesgo entre dos objetos espaciales. La Figura 2 proporciona un resumen de los casos en cuanto a algoritmos de cálculo de riesgo de colisión y como se abordan en esta tesis. Normalmente se consideran objetos esféricos para simplificar el cálculo de riesgo (caso A). Este caso está ampliamente abordado en la literatura y no se analiza en detalle en esta tesis. Un caso de ejemplo se proporciona en la sección 4.2. Considerar la forma real de los objetos (caso B) permite calcular el riesgo de una manera más precisa. Un nuevo algoritmo es definido en esta tesis para calcular el riesgo de colisión cuando al menos uno de los objetos se considera complejo (sección 4.4.2). Dicho algoritmo permite calcular el riesgo de colisión para objetos formados por un conjunto de cajas, y se ha presentado en varias conferencias internacionales. Para evaluar las prestaciones de dicho algoritmo, sus resultados se han comparado con un análisis de Monte Carlo que se ha definido para considerar colisiones entre cajas de manera adecuada (sección 4.1.2.3), pues la búsqueda de colisiones simples aplicables para objetos esféricos no es aplicable a este caso. Este análisis de Monte Carlo se considera la verdad a la hora de calcular los resultados del algoritmos, dicha comparativa se presenta en la sección 4.4.4. En el caso de satélites que no se pueden considerar esféricos, el uso de un modelo de la geometría del satélite permite descartar eventos que no son colisiones reales o estimar con mayor precisión el riesgo asociado a un evento. El uso de estos algoritmos con geometrías complejas es más relevante para objetos de dimensiones grandes debido a las prestaciones de precisión orbital actuales. En el futuro, si los sistemas de vigilancia mejoran y las órbitas son conocidas con mayor precisión, la importancia de considerar la geometría real de los satélites será cada vez más relevante. La sección 5.4 presenta un ejemplo para un sistema de grandes dimensiones (satélite con un tether). Adicionalmente, si los dos objetos involucrados en la colisión tienen velocidad relativa baja (y geometría simple, Caso C en la Figura 2), la mayor parte de los algoritmos no son aplicables requiriendo implementaciones dedicadas para este caso particular. En esta tesis, uno de estos algoritmos presentado en la literatura [Patera, 2001]R.26 se ha analizado para determinar su idoneidad en distintos tipos de eventos (sección 4.5). La evaluación frete a un análisis de Monte Carlo se proporciona en la sección 4.5.2. Tras este análisis, se ha considerado adecuado para abordar las colisiones de baja velocidad. En particular, se ha concluido que el uso de algoritmos dedicados para baja velocidad son necesarios en función del tamaño del volumen de colisión proyectado en el plano de encuentro (B-plane) y del tamaño de la incertidumbre asociada al vector posición entre los dos objetos. Para incertidumbres grandes, estos algoritmos se hacen más necesarios pues la duración del intervalo en que los elipsoides de error de los dos objetos pueden intersecar es mayor. Dicho algoritmo se ha probado integrando el algoritmo de colisión para objetos con geometrías complejas. El resultado de dicho análisis muestra que este algoritmo puede ser extendido fácilmente para considerar diferentes tipos de algoritmos de cálculo de riesgo de colisión (sección 4.5.3). Ambos algoritmos, junto con el método Monte Carlo para geometrías complejas, se han implementado en la herramienta operacional de la ESA CORAM, que es utilizada para evaluar el riesgo de colisión en las actividades rutinarias de los satélites operados por ESA [Sánchez-Ortiz, 2013a]T.11. Este hecho muestra el interés y relevancia de los algoritmos desarrollados para la mejora de las operaciones de los satélites. Dichos algoritmos han sido presentados en varias conferencias internacionales [Sánchez-Ortiz, 2013b]T.9, [Pulido, 2014]T.7,[Grande-Olalla, 2013]T.10, [Pulido, 2014]T.5, [Sánchez-Ortiz, 2015c]T.1. ABSTRACT This document addresses methodologies for computation of the collision risk of a satellite. Two different approaches need to be considered for collision risk minimisation. On an operational basis, it is needed to perform a sieve of possible objects approaching the satellite, among all objects sharing the space with an operational satellite. As the orbits of both, satellite and the eventual collider, are not perfectly known but only estimated, the miss-encounter geometry and the actual risk of collision shall be evaluated. In the basis of the encounter geometry or the risk, an eventual manoeuvre may be required to avoid the conjunction. Those manoeuvres will be associated to a reduction in the fuel for the mission orbit maintenance, and thus, may reduce the satellite operational lifetime. Thus, avoidance manoeuvre fuel budget shall be estimated, at mission design phase, for a better estimation of mission lifetime, especially for those satellites orbiting in very populated orbital regimes. These two aspects, mission design and operational collision risk aspects, are summarised in Figure 3, and covered along this thesis. Bottom part of the figure identifies the aspects to be consider for the mission design phase (statistical characterisation of the space object population data and theory computing the mean number of events and risk reduction capability) which will define the most appropriate collision avoidance approach at mission operational phase. This part is covered in this work by starting from the theory described in [Sánchez-Ortiz, 2006]T.14 and implemented by this author in ARES tool [Sánchez-Ortiz, 2004b]T.15 provided by ESA for evaluation of collision avoidance approaches. This methodology has been now extended to account for the particular features of the available data sets in operational environment (section 4.3.3). Additionally, the formulation has been extended to allow evaluating risk computation approached when orbital uncertainty is not available (like the TLE case) and when only catastrophic collisions are subject to study (section 4.3.2.3). These improvements to the theory have been included in the new version of ESA ARES tool [Domínguez-González and Sánchez-Ortiz, 2012b]T.12 and available through [SDUP,2014]R.60. At the operation phase, the real catalogue data will be processed on a routine basis, with adequate collision risk computation algorithms to propose conjunction avoidance manoeuvre optimised for every event. The optimisation of manoeuvres in an operational basis is not approached along this document. Currently, American Two Line Element (TLE) catalogue is the only public source of data providing orbits of objects in space to identify eventual conjunction events. Additionally, Conjunction Summary Message (CSM) is provided by Joint Space Operation Center (JSpOC) when the American system identifies a possible collision among satellites and debris. Depending on the data used for collision avoidance evaluation, the conjunction avoidance approach may be different. The main features of currently available data need to be analysed (in regards to accuracy) in order to perform estimation of eventual encounters to be found along the mission lifetime. In the case of TLE, as these data is not provided with accuracy information, operational collision avoidance may be also based on statistical accuracy information as the one used in the mission design approach. This is not the case for CSM data, which includes the state vector and orbital accuracy of the two involved objects. This aspect has been analysed in detail and is depicted in the document, evaluating in statistical way the characteristics of both data sets in regards to the main aspects related to collision avoidance. Once the analysis of data set was completed, investigations on the impact of those features in the most convenient avoidance approaches have been addressed (section 5.1). This analysis is published in a peer-reviewed journal [Sánchez-Ortiz, 2015b]T.3. The analysis provides recommendations for different mission types (satellite size and orbital regime) in regards to the most appropriate collision avoidance approach for relevant risk reduction. The risk reduction capability is very much dependent on the accuracy of the catalogue utilized to identify eventual collisions. Approaches based on CSM data are recommended against the TLE based approach. Some approaches based on the maximum risk associated to envisaged encounters are demonstrated to report a very large number of events, which makes the approach not suitable for operational activities. Accepted Collision Probability Levels are recommended for the definition of the avoidance strategies for different mission types. For example for the case of a LEO satellite in the Sun-synchronous regime, the typically used ACPL value of 10-4 is not a suitable value for collision avoidance schemes based on TLE data. In this case the risk reduction capacity is almost null (due to the large uncertainties associated to TLE data sets, even for short time-to-event values). For significant reduction of risk when using TLE data, ACPL on the order of 10-6 (or lower) seems to be required, producing about 10 warnings per year and mission (if one-day ahead events are considered) or 100 warnings per year (for three-days ahead estimations). Thus, the main conclusion from these results is the lack of feasibility of TLE for a proper collision avoidance approach. On the contrary, for CSM data, and due to the better accuracy of the orbital information when compared with TLE, ACPL on the order of 10-4 allows to significantly reduce the risk. This is true for events estimated up to 3 days ahead. Even 5 days ahead events can be considered, but ACPL values down to 10-5 should be considered in such case. Even larger prediction times can be considered (7 days) for risk reduction about 90%, at the cost of larger number of warnings up to 5 events per year, when 5 days prediction allows to keep the manoeuvre rate in 2 manoeuvres per year. Dynamics of the GEO orbits is different to that in LEO, impacting on a lower increase of orbits uncertainty along time. On the contrary, uncertainties at short prediction times at this orbital regime are larger than those at LEO due to the differences in observation capabilities. Additionally, it has to be accounted that short prediction times feasible at LEO may not be appropriate for a GEO mission due to the orbital period being much larger at this regime. In the case of TLE data sets, significant reduction of risk is only achieved for small ACPL values, producing about a warning event per year if warnings are raised one day in advance to the event (too short for any reaction to be considered). Suitable ACPL values would lay in between 5•10-8 and 10-7, well below the normal values used in current operations for most of the GEO missions (TLE-based strategies for collision avoidance at this regime are not recommended). On the contrary, CSM data allows a good reduction of risk with ACPL in between 10-5 and 10-4 for short and medium prediction times. 10-5 is recommended for prediction times of five or seven days. The number of events raised for a suitable warning time of seven days would be about one in a 10-year mission. It must be noted, that these results are associated to a 2 m radius spacecraft, impact of the satellite size are also analysed within the thesis. In the future, other Space Situational Awareness Systems (SSA, ESA program) may provide additional catalogues of objects in space with the aim of reducing the risk. It is needed to investigate which are the required performances of those catalogues for allowing such risk reduction. The main performance aspects are coverage (objects included in the catalogue, mainly limited by a minimum object size derived from sensor performances) and the accuracy of the orbital data to accurately evaluate the conjunctions (derived from sensor performance in regards to object observation frequency and accuracy). The results of these investigations (section 5.2) are published in a peer-reviewed journal [Sánchez-Ortiz, 2015a]T.2. This aspect was not initially foreseen as objective of the thesis, but it shows how the theory described in the thesis, initially defined for mission design in regards to avoidance manoeuvre fuel allocation (upper part of figure 1), is extended and serves for additional purposes as dimensioning a Space Surveillance and Tracking (SST) system (bottom part of figure below). The main difference between the two approaches is the consideration of the catalogue features as part of the theory which are not modified (for the satellite mission design case) instead of being an input for the analysis (in the case of the SST design). In regards to the outputs, all the features computed by the statistical conjunction analysis are of importance for mission design (with the objective of proper global avoidance strategy definition and fuel allocation), whereas for the case of SST design, the most relevant aspects are the manoeuvre and false alarm rates (defining a reliable system) and the Risk Reduction capability (driving the effectiveness of the system). In regards to the methodology for computing the risk, the SST system shall be driven by the capacity of providing the means to avoid catastrophic conjunction events (avoiding the dramatic increase of the population), whereas the satellite mission design should consider all type of encounters, as the operator is interested on avoiding both lethal and catastrophic collisions. From the analysis of the SST features (object coverage and orbital uncertainty) for a reliable system, it is concluded that those two characteristics are to be imposed differently for the different orbital regimes, as the population level is different depending on the orbit type. Coverage values range from 5 cm for very populated LEO regime up to 100 cm in the case of GEO region. The difference on this requirement derives mainly from the relative velocity of the encounters at those regimes. Regarding the orbital knowledge of the catalogues, very accurate information is required for objects in the LEO region in order to limit the number of false alarms, whereas intermediate orbital accuracy can be considered for higher orbital regimes. In regards to the operational collision avoidance approaches, several collision risk algorithms are used for evaluation of collision risk of two pair of objects. Figure 2 provides a summary of the different collision risk algorithm cases and indicates how they are covered along this document. The typical case with high relative velocity is well covered in literature for the case of spherical objects (case A), with a large number of available algorithms, that are not analysed in detailed in this work. Only a sample case is provided in section 4.2. If complex geometries are considered (Case B), a more realistic risk evaluation can be computed. New approach for the evaluation of risk in the case of complex geometries is presented in this thesis (section 4.4.2), and it has been presented in several international conferences. The developed algorithm allows evaluating the risk for complex objects formed by a set of boxes. A dedicated Monte Carlo method has also been described (section 4.1.2.3) and implemented to allow the evaluation of the actual collisions among a large number of simulation shots. This Monte Carlo runs are considered the truth for comparison of the algorithm results (section 4.4.4). For spacecrafts that cannot be considered as spheres, the consideration of the real geometry of the objects may allow to discard events which are not real conjunctions, or estimate with larger reliability the risk associated to the event. This is of particular importance for the case of large spacecrafts as the uncertainty in positions of actual catalogues does not reach small values to make a difference for the case of objects below meter size. As the tracking systems improve and the orbits of catalogued objects are known more precisely, the importance of considering actual shapes of the objects will become more relevant. The particular case of a very large system (as a tethered satellite) is analysed in section 5.4. Additionally, if the two colliding objects have low relative velocity (and simple geometries, case C in figure above), the most common collision risk algorithms fail and adequate theories need to be applied. In this document, a low relative velocity algorithm presented in the literature [Patera, 2001]R.26 is described and evaluated (section 4.5). Evaluation through comparison with Monte Carlo approach is provided in section 4.5.2. The main conclusion of this analysis is the suitability of this algorithm for the most common encounter characteristics, and thus it is selected as adequate for collision risk estimation. Its performances are evaluated in order to characterise when it can be safely used for a large variety of encounter characteristics. In particular, it is found that the need of using dedicated algorithms depend on both the size of collision volume in the B-plane and the miss-distance uncertainty. For large uncertainties, the need of such algorithms is more relevant since for small uncertainties the encounter duration where the covariance ellipsoids intersect is smaller. Additionally, its application for the case of complex satellite geometries is assessed (case D in figure above) by integrating the developed algorithm in this thesis with Patera’s formulation for low relative velocity encounters. The results of this analysis show that the algorithm can be easily extended for collision risk estimation process suitable for complex geometry objects (section 4.5.3). The two algorithms, together with the Monte Carlo method, have been implemented in the operational tool CORAM for ESA which is used for the evaluation of collision risk of ESA operated missions, [Sánchez-Ortiz, 2013a]T.11. This fact shows the interest and relevance of the developed algorithms for improvement of satellite operations. The algorithms have been presented in several international conferences, [Sánchez-Ortiz, 2013b]T.9, [Pulido, 2014]T.7,[Grande-Olalla, 2013]T.10, [Pulido, 2014]T.5, [Sánchez-Ortiz, 2015c]T.1.

Design of fast enzymes by optimizing interaction potential in active site

The diffusional encounter between substrate and enzyme, and hence catalytic efficiency, can be enhanced by mutating charged residues on the surface of the enzyme. In this paper we present a simple method for screening such mutations. This is based on our earlier result that electrostatic enhancement of the enzyme-substrate binding rate constant can be accounted for just by the interaction potential within the active site. Assuming that catalytic and structural integrity is maintained, the catalytic efficiency can be optimized by surface charge mutations which lead to stronger interaction potential within the active site. Application of the screening method on superoxide dismutase shows that only charge mutations close to the active site will have practical effect on the catalytic efficiency. This rationalizes a large number of findings obtained in previous simulation and experimental studies.

La repetición, una interpretación psicoanalítica: Freud y Lacan

The following dissertation is framed by the psychoanalytic line of thought inaugurated by Sigmund Freud and rethought by Jacques Lacan. The starting point of this work is the notion of repetition, which finds its utmost reason in what Freud called compulsive repetition. The idea of repetition, besides being called by Lacan as one of the foundations of Psychoanalysis, articulates a series of theoretical landmarks which, in turn, constitute Psychoanalysis’ own arguments – whether linked to clinical practice or articulated around metapsychological reflection of the psychoanalytical field. This dissertation is gravitates around four specific theoretical moments: two Freudian ones and two Lacanian ones. The latter taking place during the period called “The return to Freud”, which comprises the period from 1953 to 1964. In this period, the postfreudian developments deviate from Freudian theory, as well as the psychoanalytic method, which is reviewed by poststructuralism. Altogether, the four moments being analyzed are: in Freud, the “repetition linked to the act” in 1914, and the “repetition as such” developed in Beyond the Pleasure Principle in 1920.In Lacan, the theory of “the insistence of the signifier” from 1955 and what he later named as the “failed encounter with the real” in 1964...

Determining consumer satisfaction and commitment through self-service technology and personal service usage

This paper expands research into self-service technology in the service encounter. Self-service technology is where customers deliver service themselves using some form of a technological interface. There is still a great deal unknown about self-service technology, in particular its impact on consumer satisfaction and consumer commitment. With that in mind, this empirical study explores the relative impact of self-service technology on consumer satisfaction and on a multidimensional measure of consumer commitment containing affective commitment, temporal commitment and instrumental commitment. The results reveal that in a hotel context personal service still remains very important for assessments of satisfaction, and affective and temporal commitment. What is particularly interesting is that self-service technology, while impacting these constructs, also impacts instrumental commitment. This suggests that positive evaluations of self-service technology may tie consumers into relationships with hotels. A discussion and implications for managers are provided on these and other results, and the paper is concluded with further potential research.

Contextualising accounts of illness:Notions of responsibility and blame in white and South Asian respondents' accounts of diabetes causation

We undertook a secondary analysis of in-depth interviews with white (n = 32) and Pakistani and Indian (n = 32) respondents who had type 2 diabetes, which explored their perceptions and understandings of disease causation. We observed subtle, but important, differences in the ways in which these respondent groups attributed responsibility and blame for developing the disease. Whereas Pakistani and Indian respondents tended to externalise responsibility, highlighting their life circumstances in general and/or their experiences of migrating to Britain in accounting for their diabetes (or the behaviours they saw as giving rise to it), white respondents, by contrast, tended to emphasise the role of their own lifestyle 'choices' and 'personal failings'. In seeking to understand these differences, we argue for a conceptual and analytical approach which embraces both micro- (i.e. everyday) and macro- (i.e. cultural) contextual factors and experiences. In so doing, we provide a critique of social scientific studies of lay accounts/understandings of health and illness. We suggest that greater attention needs to be paid to the research encounter (that is, to who is looking at whom and in what circumstances) to understand the different kinds of contexts researchers have highlighted in presenting and interpreting their data. © 2007 Foundation for the Sociology of Health & Illness/Blackwell Publishing Ltd.

Embedding reflexivity within experiential qualitative psychology

In this article, it is argued that reflexivity is integral to experiential qualitative research in psychology. Reflexivity has been defined in many ways. Woolgar’s continuum of reflexivity though provides a useful gauge by which to judge whether a researcher is involved in simple reflection or reflexivity. The article demonstrates the benefits of adopting a reflexive attitude by presenting “challenge-to-competency.” The author’s encounter with Sarah will help illustrate the role of reflexivity both in data generation and in interpretative analysis. To close, it is proposed that reflexivity as hermeneutic reflection, with its grounding in hermeneutics and phenomenology, is a useful construct for guiding our engagement in reflexivity in experiential qualitative research.

Help-seeking for medically unexplained hearing difficulties:a qualitative study

Aims - Up to 10% of audiology patients report diffi culties hearing speech in noise even though clinical investigation reveals normal hearing thresholds, in other words, no evidence of physical pathology. The diagnostic category applied to these patients is known as King-Kopetzky Syndrome (KKS). This study aimed to gather descriptions of patients' experiences of the clinical encounter involving their KKS diagnosis and analyse the themes of help-seeking, as part of a larger study into the process of coping with medically unexplained hearing diffi culties. Method - A qualitative approach was employed, comprising unstructured interviews in the homes of 25 patients who had attended audiology services (and received a diagnosis of KKS) in Bath and Cardiff. Thematic analysis of transcripts was undertaken, infl uenced by grounded theory techniques. Findings - Informants characterized the clinical encounter as either negative or positive. Negative consultations were those in which patients' illness claims were dismissed and as such not validated. Positive encounters were typifi ed by the provision of meaningful information that reconciled clinical information with the patients' experiences of hearing loss. Conclusion - Successful management of medically unexplained illnesses requires the adoption of a patient-centred approach, rather than focusing on the absence of observable pathology

Frontline employees’ innovative service behavior as key to customer loyalty:insights into FLEs’ resource gain spiral

Many service firms require frontline service employees (FLEs) to follow routines and standardized operating procedures during the service encounter, to deliver consistently high service standards. However, to create superior, pleasurable experiences for customers, featuring both helpful services and novel approaches to meeting their needs, firms in various sectors also have begun to encourage FLEs to engage in more innovative service behaviors. This study therefore investigates a new and complementary route to customer loyalty, beyond the conventional service-profit chain, that moves through FLEs' innovative service behavior. Drawing on conservation of resources (COR) theory, this study introduces a resource gain spiral at the service encounter, which runs from FLEs' emotional job engagement to innovative service behavior, and then leads to customer delight and finally customer loyalty. In accordance with COR theory, the proposed model also includes factors that might hinder (customer aggression, underemployment) or foster (colleague support, supervisor support) FLEs' resource gain spiral. A multilevel analysis of a large-scale, dyadic data set that contains responses from both FLEs and customers in multiple industries strongly supports the proposed resource gain spiral as a complementary route to customer loyalty. The positive emotional job engagement-innovative service behavior relationship is undermined by customer aggression and underemployment, as hypothesized. Surprisingly though, and contrary to the hypotheses, colleague and supervisor support do not seem to foster FLEs' resource gain spiral. Instead, colleague support weakens the engagement-innovative service behavior relationship, and supervisor support does not affect it. These results indicate that if FLEs can solicit resources from other sources, they may not need to invest as many of their individual resources. In particular, colleague support even appears to serve as a substitute for FLEs' individual resource investments in the resource gain spiral.

Fronteras en construcción: Diferenciación social y desterritorialización en el Sur ibérico (siglos IX-VI a.C.)

Durante las tres últimas décadas, numerosos/as arqueólogos/as han discutido extensamente sobre el ritual funerario original de las poblaciones del sur ibérico entre los siglos ix y vi a.c., esto es, cremación o inhumación. Este debate está además conectado con la existencia o no de complejidad social antes de la llegada fenicia, con la aparición de una élite “orientalizada” y con la adopción de nuevos objetos y prácticas por las poblaciones locales. En este artículo hago uso del concepto deleuziano de “desterritorialización” y lo asocio con el de “frontera” desarrollado por anzaldúa para interpretar la sociedad del sur ibérico. Para ello, analizo la evidencia funeraria indígena y cuestiono la división estricta entre cremación e inhumación en la región; así como examino la profundidad y significado de los cambios funerarios en las comunidades locales.

Positronium collisions with rare-gas atoms

We calculate elastic scattering of positronium (Ps) by the Xe atom using the recently developed pseudopotential method (Fabrikant and Gribakin 2014 Phys. Rev. A 90 052717) and review general features of Ps scattering from heavier rare-gas atoms: Ar, Kr and Xe. The total scattering cross section is dominated by two contributions: elastic scattering and Ps ionization (break-up). To calculate the Ps ionization cross sections we use the binary-encounter method for Ps collisions with an atomic target. Our results for the ionization cross section agree well with previous calculations carried out in the impulse approximation. Our total Ps–Xe cross section, when plotted as a function of the projectile velocity, exhibits similarity with the electron-Xe cross section for the collision velocities higher than 0.8 a.u., and agrees very well with the measurements at Ps velocities above 0.5 a.u.

Absolute cross sections for dissociative electron attachment to HCCCN

New absolute cross sections for dissociative electron attachment to HCCCN (cyanoacetylene or propiolonitrile) in the range of 0-10 eV electron energy are presented here, which have been determined from a new analysis of previously reported data (Graupner et al 2006 New J. Phys. 8 117). The highest cross sections are observed for the formation of CN^- at 5.3 eV and CCCN^- at 5.1 eV; approximately 0.06 Ų and 0.05 Ų respectively. As part of the re-analysis, it was necessary to determine absolute cross sections for electron-impact ionization of HCCCN with the binary-encounter Bethe method. These electron-impact ionization absolute cross sections for HCCCN are also presented here; the maximum value was found to be ∼6.6 Ų at ∼80 eV.

Making British Indian Fictions, 1772-1823

This book examines fictional representations of India in novels, plays and poetry produced between the years 1772 to 1823 as historical source material. It uses literary texts as case studies to investigate how Britons residing both in the metropole and in India justified, confronted and imagined the colonial encounter during this period. The study will situate the texts in relation to the shifting colonial context and to the changing attitudes towards India within Britain in general and on the part of Britons who had experience of living in India, such as East India Company men or their wives and daughters, in particular. Moreover, it will analyse how this literature responded to the increasing influence of the subcontinent on metropolitan culture. This book, then, approaches fictional texts as case studies that illuminate trends taking place within Britain such as the growing consumption of Indian-style imported goods and the commoditisation of an Indian aesthetic within British visual culture. Whilst the book will utilise fictional portrayals to comment upon shifts in the relationship between coloniser and colonised and to discuss the cross-cultural influences between the metropole and the colonial periphery, it also outlines how literary production and print capitalism played a part in shaping depictions of the subcontinent and stereotypes of the colonial 'other'. The study will also examine how representations of the subcontinent in British art and scholarship were influenced by metropolitan literary and popular culture. At the same time it will look at how representations by metropolitan authors influenced early-nineteenth century depictions by British authors who resided in India.

Faktorer som påverkar vårdmötet mellan sjuksköterskan och föräldrar till överviktiga barn : Litteraturstudie

Bakgrund: Övervikt och fetma bland barn och ungdomar har ökat kraftigt under de senaste 20 åren. I Sverige har förekomsten av fetma ökat från 1 % till 4 %. Det finns flertalet orsaker till övervikt och fetma hos barn och ungdomar. Några av dem är genetiska faktorer, livsmedelskonsumtion, miljöfaktorer samt livsstilsfaktorer. Syfte: Att beskriva de faktorer som påverkar vårdmötet mellan sjuksköterskan och föräldrar till barn och ungdomar med övervikt eller fetma. Metod: Studien har genomförts som en litteraturöversikt och bestod av 13 artiklar. 10 med kvalitativ ansats och tre med kvantitativ ansats. Dessa hämtades i databaserna Cinahl och PubMed. Resultat: Det identifierades både hinder och möjligheter som kan uppstå i vårdmötet mellan sjuksköterskan och föräldrar. Dessa hinder och möjligheter presenteras i två kategorier med totalt fem subkategorier; Skuld och skamkänslor hos föräldrarna, förnekelse hos föräldrarna angående barnets vikt, öka medvetenheten om fördelarna med viktminskning, långsiktigt förtroende underlättar vårdmötet och anpassad kommunikation i vårdmötet mellan sjuksköterska och förälder. Slutsats: Flera faktorer identifierades som har betydelse för vårdmötet mellan sjuksköterska och föräldrar. De faktorer som utgjorde hinder i vårdmötet kan båda parter påverka så att förbättringar kan ske.

B2B-palveluprosessin analyysi ja myyntikohtaamisen kehityskohteet uusasiakashankinnassa

Tämän opinnäytetyön tavoitteena on selvittää tekijöitä, jotka vaikuttavat myyntikohtaamisen onnistumiseen potentiaalisten yritysasiakkaiden keskuudessa. Käytännön ratkaisuihin pääsemiseksi opinnäytetyössä tarkastellaan case-yritystä, joka on suomalainen vakuutusyhtiö. Tutkimus keskittyy case-yrityksen palveluprosessin tarkasteluun, sekä käytännön myyntikohtaamisen analysoimiseen. Tutkimuksen avulla pyritään muodostamaan näkemys siitä, mitä myyntikohtaamisessa kannattaa kehittää, jotta uusasiakashankintaa voitaisiin yrityksen toimintona parantaa. Myyntikohtaamista ja laajempaa palveluprosessia tarkastellaan aluksi case-yrityksen toimintamallien kautta. Keskeisessä roolissa on asiakaslähtöisen toimintaperiaatteen selventäminen teoriassa ja sen vertaaminen case-yrityksen koko palveluprosessin toimintamalleihin. Tämän jälkeen siirrytään tarkastelemaan haastattelututkimuksen avulla kerättyä dataa case-yrityksen asiakkailta. Haastattelututkimuksen avulla selvitettiin myyntikohtaamisen toteutumista käytännössä. Opinnäytetyössä selvisi, että case-yrityksen toimintamallit on rakennettu asiakaslähtöisiä periaatteita noudattaen. Myös käytännön myyntikohtaamisessa asiakaslähtöisyys toteutuu laajalti, mutta muutamia kehityskohteita etenkin ensikontaktin ja asiakkaan yksilöllisen informoinnin osalta on löydettävissä. Lisäksi case-yrityksen suositellaan kiinnittävän huomiota myyjien itsevarmuuden lisäämiseen, joka parantaa työtyytyväisyyttä, myyjien toimintavapautta ja mahdollistaa asiakaslähtöisyyden kumpuamisen organisaatiosta asiakkaalle. Opinnäytetyö jättää tilaa jatkotutkimukselle. Etenkin case-yrityksen osalta olisi suositeltavaa järjestää työtyytyväisyyskysely B2B-myyntitiimin keskuudessa, jotta toimintaa voitaisiin kehittää sisäisesti. Opinnäytetyön kehitysehdotusten pohjalta case-yritys voi myös kohdistaa lisätutkimusta asiakkaiden kokemuksiin, ja selvittää laajemman kyselyn avulla seikkoja, joita asiakkaat toivovat yritykseltä.

O desenvolvimento da competência comunicativa intercultural de surdos aprendizes de inglês : a internet como meio

Dissertação (mestrado)—Universidade de Brasília, Instituto de Letras, Departamento de Línguas Estrangeiras e Tradução, Programa de Pós-Graduação em Linguística Aplicada, 2015.