Combining static analysis and profiling for estimating execution times

Effective static analyses have been proposed which infer bounds on the number of resolutions. These have the advantage of being independent from the platform on which the programs are executed and have been shown to be useful in a number of applications, such as granularity control in parallel execution. On the other hand, in distributed computation scenarios where platforms with different capabilities come into play, it is necessary to express costs in metrics that include the characteristics of the platform. In particular, it is specially interesting to be able to infer upper and lower bounds on actual execution times. With this objective in mind, we propose an approach which combines compile-time analysis for cost bounds with a one-time profiling of a given platform in order to determine the valúes of certain parameters for that platform. These parameters calibrate a cost model which, from then on, is able to compute statically time bound functions for procedures and to predict with a significant degree of accuracy the execution times of such procedures in that concrete platform. The approach has been implemented and integrated in the CiaoPP system.

Combining static analysis and profiling for estimating execution times in logic programs

Effective static analyses have been proposed which allow inferring functions which bound the number of resolutions or reductions. These have the advantage of being independent from the platform on which the programs are executed and such bounds have been shown useful in a number of applications, such as granularity control in parallel execution. On the other hand, in certain distributed computation scenarios where different platforms come into play, with each platform having different capabilities, it is more interesting to express costs in metrics that include the characteristics of the platform. In particular, it is specially interesting to be able to infer upper and lower bounds on actual execution time. With this objective in mind, we propose a method which allows inferring upper and lower bounds on the execution times of procedures of a program in a given execution platform. The approach combines compile-time cost bounds analysis with a one-time profiling of the platform in order to determine the values of certain constants for that platform. These constants calibrate a cost model which from then on is able to compute statically time bound functions for procedures and to predict with a significant degree of accuracy the execution times of such procedures in the given platform. The approach has been implemented and integrated in the CiaoPP system.

Electron temperature versus laser intensity times wavelength squared: a comparison of theory and experiments

The peak temperature in the corona of plasma ejected by a laser-irradiated slab is discussed in terms of a one-electron-temperature model. Both heat-flux saturation and pulse rise-time effects are considered;the intensity in the rising half of the pulse is approximated by a linear function of time, I(t) = Iot/r. The temperature is found to be proportional to (IQX2)273 and a function of I0X4/r. Above a certain value of I0X4/T, the plasma presents two characteristic temperatures (at saturation and at the critical surface) which can be identified with experimentally observed cold- and hot-electron temperatures. The results are compared with extensive experimental data available for both nd and CO2 lasers, I0(W'cnf2) X2 (/um) starting around 1012. The agreement is good if substantial flux inhibition is assumed (flux-limit factor f = 0.03), and fails for I0X2 above 1O1S. Results for both ablation pressure and mass ablation rate are also given.

Optical Multistability and Oscillations in Hybrid Optical Bistable Systems with Short Delay Times

Optical instabilities in the output light from a bistable optical device (BOD) with a delayed feedback was predicted by Ikeda [1]. Gibbs et al. [2] gave the first experimental verification of this type of instabilities. From that time several groups have studied the instabilities of the BOD for different relations between the delay time tR and the time constant ح of the system. In a previous paper [3] an empirical and analytical study of instabilities in hybrid BOD was reported by us. The employed set up is shown in Fig. 1.

Old concepts for new times in photonics sensing: from inconvenient to practical

After a brief review of some old concepts getting application when new technologies have been developed, this paper offers a short review to some optical bistability concepts. It is shown how different concepts can be employed today in many fields, after being considered as inconvenient when they were found. Some practical applications and some proposals will be reported.

The Advantage of Arriving First: Characteristic Times in Finite Size Populations of Error-Prone Replicators

We study the evolution of a finite size population formed by mutationally isolated lineages of error-prone replicators in a two-peak fitness landscape. Computer simulations are performed to gain a stochastic description of the system dynamics. More specifically, for different population sizes, we compute the probability of each lineage being selected in terms of their mutation rates and the amplification factors of the fittest phenotypes. We interpret the results as the compromise between the characteristic time a lineage takes to reach its fittest phenotype by crossing the neutral valley and the selective value of the sequences that form the lineages. A main conclusion is drawn: for finite population sizes, the survival probability of the lineage that arrives first to the fittest phenotype rises significantly

Dimitris Pikionis: Roads of the Times

Dimitris Pikionis: Roads of the Times

Transit Use by Young People in Times of Financial Austerity: A Cause of Equity Concern?

This study investigates the effect of price and travel time fairness and spatial equity in transit provision on the perceived transit service quality, willingness to pay, and habitual frequency of use. Based on the theory of planned behavior, we developed a web-based questionnaire for revealed preferences data collection. The survey was administered among young people in Copenhagen and Lisbon to explore the transit perceptions and use under different economic and transit provision conditions. The survey yielded 499 questionnaires, analyzed by means of structural equation models. Results show that higher perceived fairness relates positively to higher perceived quality of transit service and higher perceived ease of paying for transit use. Higher perceived spatial equity in service provision is associated with higher perceived service quality. Higher perceived service quality relates to higher perceived ease of payment, which links to higher frequency of transit use.

Regulación del movimiento y anticipación en el resto del primer servicio en tenis

Aunque se han logrado importantes avances en estudios de laboratorio con diseños experimentales poco representativos (e.g., Farrow y Reid, 2012; Nieminen, Piirainen, Salmi, y Linnamo, 2013), a día de hoy, todavía se desconoce a cabalidad cómo los jugadores de tenis de diferente nivel de pericia calibran o ajustan sus movimientos a las demandas espacio-temporales presentes en la tarea de resto de un primer servicio. ! Escasos trabajos se han llevado a cabo in situ y a la mayoría se les puede cuestionar algún aspecto de la metodología empleada. Así pues, en varios estudios la frecuencia de grabación ha sido limitada (e.g., a 50 Hz en Jackson y Gudgeon, 2004; Triolet, Benguigui, Le Runigo y Williams, 2013), o la velocidad del saque ha sido visiblemente inferior a la habitual (cf. Carboch, Süss y Kocib, 2014; Williams, Singer y Weigelt, 1998). También, en algunos estudios los participantes experimentados no han sido jugadores de nivel internacional (e.g., Avilés, Ruiz, Sanz y Navia, 2014), y el tamaño muestral ha sido muy pequeño (e.g., Gillet, Leroy, Thouvarecq, Mégrot y Stein, 2010). ! Además, en los diferentes trabajos se han utilizado una diversidad de métodos e instrumentos de medida y los criterios de codificación del inicio de los movimientos y de las respuestas han diferido; como consecuencia el lapso visomotor de respuesta (LVMr) ha sido muy dispar variando considerablemente de 198 a 410 ms. Considerando los inconvenientes señalados anteriormente, el presente estudio tuvo como objetivo determinar un modelo técnico de regulación temporal de los movimientos y de la respuesta del restador, tomando en cuenta el flujo continuo de información proporcionado por el sacador. Para ello, se realizó un análisis cronométrico de los restos de doce jugadores de diferente nivel deportivo (seis internacionales y seis nacionales) que respondieron de forma natural enviando sus devoluciones hacia las dianas. Se grabaron las acciones de los restadores y sacadores con una cámara Casio Exilim Pro Ex-F1 de alta velocidad (300 Hz) y luego se realizó un análisis imagen por imagen cada 3.33 ms. Una vez obtenidos los datos de los vídeos se realizaron análisis con las pruebas de ANOVA de un factor, ANCOVA con la velocidad del saque como covariable, U de Mann-Whitney y Chi-cuadrado de Pearson. En cuanto a la regulación del movimiento hasta el momento del despegue, los jugadores internacionales iniciaron sus acciones antes que los jugadores nacionales lo que podría indicar una mejor preparación al ejecutar los movimientos como reflejo del nivel de pericia. Los jugadores internacionales iniciaron la elevación del pie posterior a -293 ms y los jugadores nacionales a -202 ms. Todas estas acciones se fueron enlazando unas con otras y fue en el momento del impacto del sacador donde los restadores demostraron una remarcable coordinación perceptivo-motriz. Por consiguiente, los jugadores internacionales despegaron e iniciaron el vuelo a tan solo -6.5 ms del impacto y los jugadores nacionales lo hicieron más tarde a +19.5 ms. A lo largo de la secuencia temporal, todo parece indicar que las informaciones que utilizan los restadores interactúan entre sí; información más temprana y menos fiable para anticipar o moverse antes e información más tardía y más fiable para regular la temporalización de las acciones. Los restadores de nivel internacional y nacional anticiparon a nivel espacial en un bajo porcentaje (7.7% vs. 13.6%) y en tiempos similares (-127 vs. -118 ms) sugiriendo que la utilización de variables ópticas tempranas y menos fiables solo se produce en contadas ocasiones. Por otra parte, estos datos se relacionan con una gran precisión en la respuesta ya que tanto los jugadores internacionales como los nacionales demostraron un alto porcentaje de acierto al responder (95.4% vs. 96.7%). Se había señalado que los jugadores internacionales y nacionales se diferenciarían en el tiempo de caída (i.e., aterrizaje) del primer pie del salto preparatorio, sin embargo ese efecto no fue encontrado (128 vs. 135 ms). Tampoco se hallaron diferencias en el porcentaje de caída con el pie contrario a la dirección de la pelota (58% vs. 62%). Donde sí ambos grupos se diferenciaron fue en el tiempo de caída del segundo pie (147 vs. 168 ms). Esta diferencia de 21 ms fue crucial y fue una prueba de la mayor rapidez de los jugadores internacionales; sugiriendo que ésta acción se podría relacionar con el momento del inicio de la respuesta. Aunque los jugadores internacionales hayan demostrado ser más rápidos en relación con sus capacidades funcionales, ambos grupos no se diferenciaron en todas las variables relacionadas con el LVMr. Ellos no utilizaron esos valiosos milisegundos ganados en el instante de la caída del segundo pie para responder más pronto, ya que el LVMr del miembro superior fue el mismo para ambos grupos (179 vs. 174 ms). Es como si hubiesen tenido todo el tiempo del mundo para seguir ajustando sus acciones hasta el propio golpeo. Además, estos tiempos largos sugieren que en la gran mayoría de los restos la información clave que determinó la respuesta fue detectada (extraída) en momentos cercanos al golpeo del sacador y en la primera parte del vuelo de la pelota. Asimismo, se constató que en general el LVMr se ve influenciado por el tipo de información utilizada. De esta manera, cuando se tomaron en cuenta los ensayos en los que hubo anticipación espacial reflejados en el LVMr del cuerpo entero los tiempos disminuyeron (152 vs. 136 ms). Por otra parte, existieron ocasiones (13%) en los que tanto los jugadores internacionales como los nacionales respondieron tarde recibiendo saques directos (208 vs. 195 ms). Es muy posible que en estos casos los jugadores hayan tenido problemas para detectar la información respondiendo fuera de los márgenes temporales de acción lo que mermó su rendimiento. Lo mismo pudo haber ocurrido cuando ambos grupos de jugadores corrigieron el movimiento del miembro superior tras el impacto (17% vs. 10%) lo que aumentó el tiempo en responder al redirigir la respuesta hacia el lado correcto (208 vs. 205 ms). Además, los jugadores internacionales obtuvieron tiempos de movimiento menores que el de los jugadores nacionales (509 vs. 531 ms) lo que se reflejó en un tiempo total de actuación menor (683 vs. 703 ms). Por último, en cuanto al rendimiento del resto, los jugadores internacionales obtuvieron valores superiores a los jugadores nacionales (1.3 vs. 0.9). ABSTRACT Although there have been significant advances in laboratory studies with unrepresentative experimental designs (e.g., Farrow y Reid, 2012; Nieminen, Piirainen, Salmi, y Linnamo, 2013), today it is still unknown to full extent how tennis players of different levels of expertise calibrate or adjust their movements to the spatial-temporal demands present in the return of a first serve. Few studies have been carried out in situ and some aspects of the methodology most of them used can be questioned. Thus, in several studies the recording frequency has been limited (e.g., a 50 Hz en Jackson y Gudgeon, 2004; Triolet, Benguigui, Le Runigo y Williams, 2013), or serve speed was visibly lower than the usual one (cf. Carboch, Süss y Kocib, 2014; Williams, Singer y Weigelt, 1998). Also, in some studies, experienced participants have not played at international level (e.g., Avilés, Ruiz, Sanz y Navia, 2014), and the sample size has been very small (e.g., Gillet, Leroy, Thouvarecq, Mégrot y Stein, 2010). Furthermore, different works have used a variety of methods and measurement instruments and coding criteria of the onset of movements and responses have differed; due to this, visuomotor response delay (LVMr) has been very uneven, varying considerably from 198-410 ms. Considering the drawbacks mentioned above, this study aimed to determine a technical model of temporal regulation of movements and returner’s response, taking into account the continuous flow of information provided by the server. For this, a chronometric analysis of the returns of twelve players (six international and six national) of different sports level, that naturally responded by hitting their returns towards the targets, was performed. Actions of servers and returners were recorded with a Casio Exilim Pro Ex-F1 high speed camera (300 Hz) and then every 3.33 ms analysis was made frame by frame. Once the data of the videos were obtained, analyses were performed using one factor ANOVA test, ANCOVA with the speed of the serve as a covariate, U of Mann- Whitney and Pearson’s Chi-square test. As for the regulation of movement until the moment of serve, international players began their actions before national players, which could indicate that they were better prepared to execute movements reflecting the level of their expertise. International players began raising the rear foot at -293 ms and national players at -202 ms. All these actions were being linked to each other and it was at the moment of impact of the server when the receivers demonstrated a remarkable perceptual-motor coordination. Therefore, international players took off and started their flight just -6.5 ms before the serve and national players did the same somewhat later: +19.5 ms after the serve. Along the timeline, everything seems to indicate that the information used by returners interact with each other; early information which is less reliable to anticipate or move before, and later information more reliable appears to regulate the timing of actions. Returners of international and national levels anticipated at spatial level in a low percentage (7.7% vs. 13.6%) and in similar times (-127 vs. -118 ms) suggesting that the use of early and less reliable optical variables is only produced on rare occasions. Moreover, these data relate to a precise response as both international and national players showed a high percentage of success in responding (95.4% vs. 96.7%). It had been noted that international and national players would differ in the time the fall (i.e., landing) of the first foot of the split-step, however, this effect was not found (128 vs. 135 ms). No differences in the percentage of fall with the opposite foot to the direction of the ball (58% vs. 62%) were found. Where the two groups differed was in the time of the fall of the second foot (147 vs. 168 ms). This difference of 21 ms was crucial and it was a proof of mayor speed of international players; suggesting that this action could be related to the onset time of response. Although international players have proven to be faster in relation to their functional capabilities, both groups did not differ in all variables related to LVMr. They did not use those precious milliseconds earned at the time of the fall of the second foot to respond as soon, since the LVMr of the upper limb was the same for both groups (179 vs. 174 ms). It is as if they had all the time in the world to continue to adjust their actions until the return itself. Furthermore, these long times suggest that in the vast majority of the returns, key information that determined the response was detected (pick-up) in moments close to the hit of the server and in the first part of the ball flight. It was also found that in general the LVMr is influenced by the type of information used. Thus, when taking into account the trials during which there was spatial anticipation, reflected in LVMr of the whole body, the times decreased (152 vs. 136 ms). On the other hand, there were occasions (13%) where both international and national players responded late, thus receiving aces (208 vs. 195 ms). It is quite possible that in these cases the players have had trouble to pick-up information, responding out of temporary margins of action, which affected their performance. The same could have occurred when both groups of players corrected upper limb movement after impact (17% vs. 10%), which increased the time to respond and to redirect the return towards the right side (208 vs. 205 ms). Moreover, international players scored lower movement times than the national players (509 vs. 531 ms), which was reflected in a shorter total response time (683 vs. 703 ms). Finally, as far as the performance of return is concerned, international players scored above the national players values (1.3 vs. 0.9).

Optimization of the Integrated Guidance and Control for a Dual Aerodynamic Control Missile

Las futuras misiones para misiles aire-aire operando dentro de la atmósfera requieren la interceptación de blancos a mayores velocidades y más maniobrables, incluyendo los esperados vehículos aéreos de combate no tripulados. La intercepción tiene que lograrse desde cualquier ángulo de lanzamiento. Una de las principales discusiones en la tecnología de misiles en la actualidad es cómo satisfacer estos nuevos requisitos incrementando la capacidad de maniobra del misil y en paralelo, a través de mejoras en los métodos de guiado y control modernos. Esta Tesis aborda estos dos objetivos simultáneamente, al proponer un diseño integrando el guiado y el control de vuelo (autopiloto) y aplicarlo a misiles con control aerodinámico simultáneo en canard y cola. Un primer avance de los resultados obtenidos ha sido publicado recientemente en el Journal of Aerospace Engineering, en Abril de 2015, [Ibarrondo y Sanz-Aranguez, 2015]. El valor del diseño integrado obtenido es que permite al misil cumplir con los requisitos operacionales mencionados empleando únicamente control aerodinámico. El diseño propuesto se compara favorablemente con esquemas más tradicionales, consiguiendo menores distancias de paso al blanco y necesitando de menores esfuerzos de control incluso en presencia de ruidos. En esta Tesis se demostrará cómo la introducción del doble mando, donde tanto el canard como las aletas de cola son móviles, puede mejorar las actuaciones de un misil existente. Comparado con un misil con control en cola, el doble control requiere sólo introducir dos servos adicionales para accionar los canards también en guiñada y cabeceo. La sección de cola será responsable de controlar el misil en balanceo mediante deflexiones diferenciales de los controles. En el caso del doble mando, la complicación añadida es que los vórtices desprendidos de los canards se propagan corriente abajo y pueden incidir sobre las superficies de cola, alterando sus características de control. Como un primer aporte, se ha desarrollado un modelo analítico completo para la aerodinámica no lineal de un misil con doble control, incluyendo la caracterización de este efecto de acoplamiento aerodinámico. Hay dos modos de funcionamiento en picado y guiñada para un misil de doble mando: ”desviación” y ”opuesto”. En modo ”desviación”, los controles actúan en la misma dirección, generando un cambio inmediato en la sustentación y produciendo un movimiento de translación en el misil. La respuesta es rápida, pero en el modo ”desviación” los misiles con doble control pueden tener dificultades para alcanzar grandes ángulos de ataque y altas aceleraciones laterales. Cuando los controles actúan en direcciones opuestas, el misil rota y el ángulo de ataque del fuselaje se incrementa para generar mayores aceleraciones en estado estacionario, aunque el tiempo de respuesta es mayor. Con el modelo aerodinámico completo, es posible obtener una parametrización dependiente de los estados de la dinámica de corto periodo del misil. Debido al efecto de acoplamiento entre los controles, la respuesta en bucle abierto no depende linealmente de los controles. El autopiloto se optimiza para obtener la maniobra requerida por la ley de guiado sin exceder ninguno de los límites aerodinámicos o mecánicos del misil. Una segunda contribución de la tesis es el desarrollo de un autopiloto con múltiples entradas de control y que integra la aerodinámica no lineal, controlando los tres canales de picado, guiñada y cabeceo de forma simultánea. Las ganancias del autopiloto dependen de los estados del misil y se calculan a cada paso de integración mediante la resolución de una ecuación de Riccati de orden 21x21. Las ganancias obtenidas son sub-óptimas, debido a que una solución completa de la ecuación de Hamilton-Jacobi-Bellman no puede obtenerse de manera práctica, y se asumen ciertas simplificaciones. Se incorpora asimismo un mecanismo que permite acelerar la respuesta en caso necesario. Como parte del autopiloto, se define una estrategia para repartir el esfuerzo de control entre el canard y la cola. Esto se consigue mediante un controlador aumentado situado antes del bucle de optimización, que minimiza el esfuerzo total de control para maniobrar. Esta ley de alimentación directa mantiene al misil cerca de sus condiciones de equilibrio, garantizando una respuesta transitoria adecuada. El controlador no lineal elimina la respuesta de fase no-mínima característica de la cola. En esta Tesis se consideran dos diseños para el guiado y control, el control en Doble-Lazo y el control Integrado. En la aproximación de Doble-Lazo, el autopiloto se sitúa dentro de un bucle interior y se diseña independientemente del guiado, que conforma el bucle más exterior del control. Esta estructura asume que existe separación espectral entre los dos, esto es, que los tiempos de respuesta del autopiloto son mucho mayores que los tiempos característicos del guiado. En el estudio se combina el autopiloto desarrollado con una ley de guiado óptimo. Los resultados obtenidos demuestran que se consiguen aumentos muy importantes en las actuaciones frente a misiles con control canard o control en cola, y que la interceptación, cuando se lanza cerca del curso de colisión, se consigue desde cualquier ángulo alrededor del blanco. Para el misil de doble mando, la estrategia óptima resulta en utilizar el modo de control opuesto en la aproximación al blanco y utilizar el modo de desviación justo antes del impacto. Sin embargo la lógica de doble bucle no consigue el impacto cuando hay desviaciones importantes con respecto al curso de colisión. Una de las razones es que parte de la demanda de guiado se pierde, ya que el misil solo es capaz de modificar su aceleración lateral, y no tiene control sobre su aceleración axial, a no ser que incorpore un motor de empuje regulable. La hipótesis de separación mencionada, y que constituye la base del Doble-Bucle, puede no ser aplicable cuando la dinámica del misil es muy alta en las proximidades del blanco. Si se combinan el guiado y el autopiloto en un único bucle, la información de los estados del misil está disponible para el cálculo de la ley de guiado, y puede calcularse la estrategia optima de guiado considerando las capacidades y la actitud del misil. Una tercera contribución de la Tesis es la resolución de este segundo diseño, la integración no lineal del guiado y del autopiloto (IGA) para el misil de doble control. Aproximaciones anteriores en la literatura han planteado este sistema en ejes cuerpo, resultando en un sistema muy inestable debido al bajo amortiguamiento del misil en cabeceo y guiñada. Las simplificaciones que se tomaron también causan que el misil se deslice alrededor del blanco y no consiga la intercepción. En nuestra aproximación el problema se plantea en ejes inerciales y se recurre a la dinámica de los cuaterniones, eliminado estos inconvenientes. No se limita a la dinámica de corto periodo del misil, porque se construye incluyendo de modo explícito la velocidad dentro del bucle de optimización. La formulación resultante en el IGA es independiente de la maniobra del blanco, que sin embargo se ha de incluir en el cálculo del modelo en Doble-bucle. Un típico inconveniente de los sistemas integrados con controlador proporcional, es el problema de las escalas. Los errores de guiado dominan sobre los errores de posición del misil y saturan el controlador, provocando la pérdida del misil. Este problema se ha tratado aquí con un controlador aumentado previo al bucle de optimización, que define un estado de equilibrio local para el sistema integrado, que pasa a actuar como un regulador. Los criterios de actuaciones para el IGA son los mismos que para el sistema de Doble-Bucle. Sin embargo el problema matemático resultante es muy complejo. El problema óptimo para tiempo finito resulta en una ecuación diferencial de Riccati con condiciones terminales, que no puede resolverse. Mediante un cambio de variable y la introducción de una matriz de transición, este problema se transforma en una ecuación diferencial de Lyapunov que puede resolverse mediante métodos numéricos. La solución resultante solo es aplicable en un entorno cercano del blanco. Cuando la distancia entre misil y blanco es mayor, se desarrolla una solución aproximada basada en la solución de una ecuación algebraica de Riccati para cada paso de integración. Los resultados que se han obtenido demuestran, a través de análisis numéricos en distintos escenarios, que la solución integrada es mejor que el sistema de Doble-Bucle. Las trayectorias resultantes son muy distintas. El IGA preserva el guiado del misil y consigue maximizar el uso de la propulsión, consiguiendo la interceptación del blanco en menores tiempos de vuelo. El sistema es capaz de lograr el impacto donde el Doble-Bucle falla, y además requiere un orden menos de magnitud en la cantidad de cálculos necesarios. El efecto de los ruidos radar, datos discretos y errores del radomo se investigan. El IGA es más robusto, resultando menos afectado por perturbaciones que el Doble- Bucle, especialmente porque el núcleo de optimización en el IGA es independiente de la maniobra del blanco. La estimación de la maniobra del blanco es siempre imprecisa y contaminada por ruido, y degrada la precisión de la solución de Doble-Bucle. Finalmente, como una cuarta contribución, se demuestra que el misil con guiado IGA es capaz de realizar una maniobra de defensa contra un blanco que ataque por su cola, sólo con control aerodinámico. Las trayectorias estudiadas consideran una fase pre-programada de alta velocidad de giro, manteniendo siempre el misil dentro de su envuelta de vuelo. Este procedimiento no necesita recurrir a soluciones técnicamente más complejas como el control vectorial del empuje o control por chorro para ejecutar esta maniobra. En todas las demostraciones matemáticas se utiliza el producto de Kronecker como una herramienta practica para manejar las parametrizaciones dependientes de variables, que resultan en matrices de grandes dimensiones. ABSTRACT Future missions for air to air endo-atmospheric missiles require the interception of targets with higher speeds and more maneuverable, including forthcoming unmanned supersonic combat vehicles. The interception will need to be achieved from any angle and off-boresight launch conditions. One of the most significant discussions in missile technology today is how to satisfy these new operational requirements by increasing missile maneuvering capabilities and in parallel, through the development of more advanced guidance and control methods. This Thesis addresses these two objectives by proposing a novel optimal integrated guidance and autopilot design scheme, applicable to more maneuverable missiles with forward and rearward aerodynamic controls. A first insight of these results have been recently published in the Journal of Aerospace Engineering in April 2015, [Ibarrondo and Sanz-Aránguez, 2015]. The value of this integrated solution is that it allows the missile to comply with the aforementioned requirements only by applying aerodynamic control. The proposed design is compared against more traditional guidance and control approaches with positive results, achieving reduced control efforts and lower miss distances with the integrated logic even in the presence of noises. In this Thesis it will be demonstrated how the dual control missile, where canard and tail fins are both movable, can enhance the capabilities of an existing missile airframe. Compared to a tail missile, dual control only requires two additional servos to actuate the canards in pitch and yaw. The tail section will be responsible to maintain the missile stabilized in roll, like in a classic tail missile. The additional complexity is that the vortices shed from the canard propagate downstream where they interact with the tail surfaces, altering the tail expected control characteristics. These aerodynamic phenomena must be properly described, as a preliminary step, with high enough precision for advanced guidance and control studies. As a first contribution we have developed a full analytical model of the nonlinear aerodynamics of a missile with dual control, including the characterization of this cross-control coupling effect. This development has been produced from a theoretical model validated with reliable practical data obtained from wind tunnel experiments available in the scientific literature, complement with computer fluid dynamics and semi-experimental methods. There are two modes of operating a missile with forward and rear controls, ”divert” and ”opposite” modes. In divert mode, controls are deflected in the same direction, generating an increment in direct lift and missile translation. Response is fast, but in this mode, dual control missiles may have difficulties in achieving large angles of attack and high level of lateral accelerations. When controls are deflected in opposite directions (opposite mode) the missile airframe rotates and the body angle of attack is increased to generate greater accelerations in steady-state, although the response time is larger. With the aero-model, a state dependent parametrization of the dual control missile short term dynamics can be obtained. Due to the cross-coupling effect, the open loop dynamics for the dual control missile is not linearly dependent of the fin positions. The short term missile dynamics are blended with the servo system to obtain an extended autopilot model, where the response is linear with the control fins turning rates, that will be the control variables. The flight control loop is optimized to achieve the maneuver required by the guidance law without exceeding any of the missile aerodynamic or mechanical limitations. The specific aero-limitations and relevant performance indicators for the dual control are set as part of the analysis. A second contribution of this Thesis is the development of a step-tracking multi-input autopilot that integrates non-linear aerodynamics. The designed dual control missile autopilot is a full three dimensional autopilot, where roll, pitch and yaw are integrated, calculating command inputs simultaneously. The autopilot control gains are state dependent, and calculated at each integration step solving a matrix Riccati equation of order 21x21. The resulting gains are sub-optimal as a full solution for the Hamilton-Jacobi-Bellman equation cannot be resolved in practical terms and some simplifications are taken. Acceleration mechanisms with an λ-shift is incorporated in the design. As part of the autopilot, a strategy is defined for proper allocation of control effort between canard and tail channels. This is achieved with an augmented feed forward controller that minimizes the total control effort of the missile to maneuver. The feedforward law also maintains the missile near trim conditions, obtaining a well manner response of the missile. The nonlinear controller proves to eliminate the non-minimum phase effect of the tail. Two guidance and control designs have been considered in this Thesis: the Two- Loop and the Integrated approaches. In the Two-Loop approach, the autopilot is placed in an inner loop and designed separately from an outer guidance loop. This structure assumes that spectral separation holds, meaning that the autopilot response times are much higher than the guidance command updates. The developed nonlinear autopilot is linked in the study to an optimal guidance law. Simulations are carried on launching close to collision course against supersonic and highly maneuver targets. Results demonstrate a large boost in performance provided by the dual control versus more traditional canard and tail missiles, where interception with the dual control close to collision course is achieved form 365deg all around the target. It is shown that for the dual control missile the optimal flight strategy results in using opposite control in its approach to target and quick corrections with divert just before impact. However the Two-Loop logic fails to achieve target interception when there are large deviations initially from collision course. One of the reasons is that part of the guidance command is not followed, because the missile is not able to control its axial acceleration without a throttleable engine. Also the separation hypothesis may not be applicable for a high dynamic vehicle like a dual control missile approaching a maneuvering target. If the guidance and autopilot are combined into a single loop, the guidance law will have information of the missile states and could calculate the most optimal approach to the target considering the actual capabilities and attitude of the missile. A third contribution of this Thesis is the resolution of the mentioned second design, the non-linear integrated guidance and autopilot (IGA) problem for the dual control missile. Previous approaches in the literature have posed the problem in body axes, resulting in high unstable behavior due to the low damping of the missile, and have also caused the missile to slide around the target and not actually hitting it. The IGA system is posed here in inertial axes and quaternion dynamics, eliminating these inconveniences. It is not restricted to the missile short term dynamic, and we have explicitly included the missile speed as a state variable. The IGA formulation is also independent of the target maneuver model that is explicitly included in the Two-loop optimal guidance law model. A typical problem of the integrated systems with a proportional control law is the problem of scales. The guidance errors are larger than missile state errors during most of the flight and result in high gains, control saturation and loss of control. It has been addressed here with an integrated feedforward controller that defines a local equilibrium state at each flight point and the controller acts as a regulator to minimize the IGA states excursions versus the defined feedforward state. The performance criteria for the IGA are the same as in the Two-Loop case. However the resulting optimization problem is mathematically very complex. The optimal problem in a finite-time horizon results in an irresoluble state dependent differential Riccati equation with terminal conditions. With a change of variable and the introduction of a transition matrix, the equation is transformed into a time differential Lyapunov equation that can be solved with known numerical methods in real time. This solution results range limited, and applicable when the missile is in a close neighborhood of the target. For larger ranges, an approximate solution is used, obtained from solution of an algebraic matrix Riccati equation at each integration step. The results obtained show, by mean of several comparative numerical tests in diverse homing scenarios, than the integrated approach is a better solution that the Two- Loop scheme. Trajectories obtained are very different in the two cases. The IGA fully preserves the guidance command and it is able to maximize the utilization of the missile propulsion system, achieving interception with lower miss distances and in lower flight times. The IGA can achieve interception against off-boresight targets where the Two- Loop was not able to success. As an additional advantage, the IGA also requires one order of magnitude less calculations than the Two-Loop solution. The effects of radar noises, discrete radar data and radome errors are investigated. IGA solution is robust, and less affected by radar than the Two-Loop, especially because the target maneuvers are not part of the IGA core optimization loop. Estimation of target acceleration is always imprecise and noisy and degrade the performance of the two-Loop solution. The IGA trajectories are such that minimize the impact of radome errors in the guidance loop. Finally, as a fourth contribution, it is demonstrated that the missile with IGA guidance is capable of performing a defense against attacks from its rear hemisphere, as a tail attack, only with aerodynamic control. The studied trajectories have a preprogrammed high rate turn maneuver, maintaining the missile within its controllable envelope. This solution does not recur to more complex features in service today, like vector control of the missile thrust or side thrusters. In all the mathematical treatments and demonstrations, the Kronecker product has been introduced as a practical tool to handle the state dependent parametrizations that have resulted in very high order matrix equations.