The aim of this Doctoral Thesis is to develop a genetic algorithm based optimization methods to find the best conceptual design architecture of an aero-piston-engine, for given design specifications. Nowadays, the conceptual design of turbine airplanes starts with the aircraft specifications, then the most suited turbofan or turbo propeller for the specific application is chosen. In the aeronautical piston engines field, which has been dormant for several decades, as interest shifted towards turboaircraft, new materials with increased performance and properties have opened new possibilities for development. Moreover, the engine’s modularity given by the cylinder unit, makes it possible to design a specific engine for a given application. In many real engineering problems the amount of design variables may be very high, characterized by several non-linearities needed to describe the behaviour of the phenomena. In this case the objective function has many local extremes, but the designer is usually interested in the global one. The stochastic and the evolutionary optimization techniques, such as the genetic algorithms method, may offer reliable solutions to the design problems, within acceptable computational time. The optimization algorithm developed here can be employed in the first phase of the preliminary project of an aeronautical piston engine design. It’s a mono-objective genetic algorithm, which, starting from the given design specifications, finds the engine propulsive system configuration which possesses minimum mass while satisfying the geometrical, structural and performance constraints. The algorithm reads the project specifications as input data, namely the maximum values of crankshaft and propeller shaft speed and the maximal pressure value in the combustion chamber. The design variables bounds, that describe the solution domain from the geometrical point of view, are introduced too. In the Matlab® Optimization environment the objective function to be minimized is defined as the sum of the masses of the engine propulsive components. Each individual that is generated by the genetic algorithm is the assembly of the flywheel, the vibration damper and so many pistons, connecting rods, cranks, as the number of the cylinders. The fitness is evaluated for each individual of the population, then the rules of the genetic operators are applied, such as reproduction, mutation, selection, crossover. In the reproduction step the elitist method is applied, in order to save the fittest individuals from a contingent mutation and recombination disruption, making it undamaged survive until the next generation. Finally, as the best individual is found, the optimal dimensions values of the components are saved to an Excel® file, in order to build a CAD-automatic-3D-model for each component of the propulsive system, having a direct pre-visualization of the final product, still in the engine’s preliminary project design phase. With the purpose of showing the performance of the algorithm and validating this optimization method, an actual engine is taken, as a case study: it’s the 1900 JTD Fiat Avio, 4 cylinders, 4T, Diesel. Many verifications are made on the mechanical components of the engine, in order to test their feasibility and to decide their survival through generations. A system of inequalities is used to describe the non-linear relations between the design variables, and is used for components checking for static and dynamic loads configurations. The design variables geometrical boundaries are taken from actual engines data and similar design cases. Among the many simulations run for algorithm testing, twelve of them have been chosen as representative of the distribution of the individuals. Then, as an example, for each simulation, the corresponding 3D models of the crankshaft and the connecting rod, have been automatically built. In spite of morphological differences among the component the mass is almost the same. The results show a significant mass reduction (almost 20% for the crankshaft) in comparison to the original configuration, and an acceptable robustness of the method have been shown. The algorithm here developed is shown to be a valid method for an aeronautical-piston-engine preliminary project design optimization. In particular the procedure is able to analyze quite a wide range of design solutions, rejecting the ones that cannot fulfill the feasibility design specifications. This optimization algorithm could increase the aeronautical-piston-engine development, speeding up the production rate and joining modern computation performances and technological awareness to the long lasting traditional design experiences.

Ground-based Earth troposphere calibration systems play an important role in planetary exploration, especially to carry out radio science experiments aimed at the estimation of planetary gravity fields. In these experiments, the main observable is the spacecraft (S/C) range rate, measured from the Doppler shift of an electromagnetic wave transmitted from ground, received by the spacecraft and coherently retransmitted back to ground. If the solar corona and interplanetary plasma noise is already removed from Doppler data, the Earth troposphere remains one of the main error sources in tracking observables. Current Earth media calibration systems at NASA’s Deep Space Network (DSN) stations are based upon a combination of weather data and multidirectional, dual frequency GPS measurements acquired at each station complex. In order to support Cassini’s cruise radio science experiments, a new generation of media calibration systems were developed, driven by the need to achieve the goal of an end-to-end Allan deviation of the radio link in the order of 3×〖10〗^(-15) at 1000 s integration time. The future ESA’s Bepi Colombo mission to Mercury carries scientific instrumentation for radio science experiments (a Ka-band transponder and a three-axis accelerometer) which, in combination with the S/C telecommunication system (a X/X/Ka transponder) will provide the most advanced tracking system ever flown on an interplanetary probe. Current error budget for MORE (Mercury Orbiter Radioscience Experiment) allows the residual uncalibrated troposphere to contribute with a value of 8×〖10〗^(-15) to the two-way Allan deviation at 1000 s integration time. The current standard ESA/ESTRACK calibration system is based on a combination of surface meteorological measurements and mathematical algorithms, capable to reconstruct the Earth troposphere path delay, leaving an uncalibrated component of about 1-2% of the total delay. In order to satisfy the stringent MORE requirements, the short time-scale variations of the Earth troposphere water vapor content must be calibrated at ESA deep space antennas (DSA) with more precise and stable instruments (microwave radiometers). In parallel to this high performance instruments, ESA ground stations should be upgraded to media calibration systems at least capable to calibrate both troposphere path delay components (dry and wet) at sub-centimetre level, in order to reduce S/C navigation uncertainties. The natural choice is to provide a continuous troposphere calibration by processing GNSS data acquired at each complex by dual frequency receivers already installed for station location purposes. The work presented here outlines the troposphere calibration technique to support both Deep Space probe navigation and radio science experiments. After an introduction to deep space tracking techniques, observables and error sources, in Chapter 2 the troposphere path delay is widely investigated, reporting the estimation techniques and the state of the art of the ESA and NASA troposphere calibrations. Chapter 3 deals with an analysis of the status and the performances of the NASA Advanced Media Calibration (AMC) system referred to the Cassini data analysis. Chapter 4 describes the current release of a developed GNSS software (S/W) to estimate the troposphere calibration to be used for ESA S/C navigation purposes. During the development phase of the S/W a test campaign has been undertaken in order to evaluate the S/W performances. A description of the campaign and the main results are reported in Chapter 5. Chapter 6 presents a preliminary analysis of microwave radiometers to be used to support radio science experiments. The analysis has been carried out considering radiometric measurements of the ESA/ESTEC instruments installed in Cabauw (NL) and compared with the requirements of MORE. Finally, Chapter 7 summarizes the results obtained and defines some key technical aspects to be evaluated and taken into account for the development phase of future instrumentation.

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In the framework of developing defect-based life models, in which breakdown is explicitly associated with partial discharge (PD)-induced damage growth from a defect, ageing tests and PD measurements were carried out in the lab on polyethylene (PE) layered specimens containing artificial cavities. PD activity was monitored continuously during aging. A quasi-deterministic series of stages can be observed in the behavior of the main PD parameters (i.e. discharge repetition rate and amplitude). Phase-resolved PD patterns at various ageing stages were reproduced by numerical simulation which is based on a physical discharge model devoid of adaptive parameters. The evolution of the simulation parameters provides insight into the physical-chemical changes taking place at the dielectric/cavity interface during the aging process. PD activity shows similar time behavior under constant cavity gas volume and constant cavity gas pressure conditions, suggesting that the variation of PD parameters may not be attributed to the variation of the gas pressure. Brownish PD byproducts, consisting of oxygen containing moieties, and degradation pits were found at the dielectric/cavity interface. It is speculated that the change of PD activity is related to the composition of the cavity gas, as well as to the properties of dielectric/cavity interface.

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In this PhD thesis the crashworthiness topic is studied with the perspective of the development of a small-scale experimental test able to characterize a material in terms of energy absorption. The material properties obtained are then used to validate a nu- merical model of the experimental test itself. Consequently, the numerical model, calibrated on the specific ma- terial, can be extended to more complex structures and used to simulate their energy absorption behavior. The experimental activity started at University of Washington in Seattle, WA (USA) and continued at Second Faculty of Engi- neering, University of Bologna, Forl`ı (Italy), where the numerical model for the simulation of the experimental test was implemented and optimized.

La tematica del presente scritto è l’analisi teorico-sperimentale del sistema edificio-impianto, che è funzione delle soluzioni progettuali adottate, dei componenti scelti e del tipo di conduzione prevista. La Direttiva 2010/31/CE sulle prestazioni energetiche degli edifici, entrata in vigore l’8 luglio 2010, pubblicata sulla Gazzetta Europea del 18 giugno 2010, sostituirà, dal 1º febbraio 2012, la direttiva 2002/91/CE. La direttiva prevede che vengano redatti piani nazionali destinati ad aumentare il numero di “edifici a energia quasi zero” e che entro il 31 dicembre 2020 tutti gli edifici di nuova costruzione dovranno essere “edifici a energia quasi zero”, per gli edifici pubblici questa scadenza è anticipata al 31 dicembre 2018. In questa prospettiva sono stati progettati due “edifici a energia quasi zero”, una villa monofamiliare e un complesso scolastico (scuola dell’infanzia, elementare, media inferiore) attualmente in via di realizzazione, con l’obiettivo principale di fornire un caso studio unico per ogni tipologia in quanto anche modulare e replicabile nella realtà del nostro territorio, che anticipano gli obiettivi fissati dalla Direttiva 2010/31/CE. I risultati ottenibili dai suddetti progetti, esposti nella tesi, sono il frutto di un attenta e proficua progettazione integrata, connubio tra progettazione architettonica ed energetico/impiantistica. La stessa progettazione ha esaminato le tecnologie, i materiali e le soluzioni tecniche “mirate” ai fini del comfort ambientale e di un’elevata prestazione energetica dell’edificio. Inoltre è stato dedicato ampio rilievo alla diagnosi energetica degli edifici esistenti attraverso 4 casi studio, i principali svolti durante i tre anni di dottorato di ricerca, esemplari del patrimonio edilizio italiano. Per ogni caso studio è stata condotta una diagnosi energetica dell’edificio, valutati i risultati e definita la classe energetica, ed in seguito sono stati presi in considerazione i possibili interventi migliorativi sia da un punto di vista qualitativo sia economico tenendo conto degli incentivi statali per l’incremento dell’efficienza energetica.

This thesis was carried out in the context of a co-tutoring program between Centro Ceramico Bologna (Italy) and Instituto di Tecnologia Ceramica, Castellón de la Plana (Spain). The subject of the thesis is the synthesis of silver nanoparticles and at their likely decorative application in the productive process of porcelain ceramic tiles. Silver nanoparticles were chosen as a case study, because metal nanoparticles are thermally stable, and they have non-linear optical properties when nano-structured, and therefore they develop saturated colours. The nanoparticles were synthesized by chemical reduction in aqueous solution, a method chosen because of its reduced working steps and energy costs. Besides such a synthesis method uses non-expensive and non-toxic raw material. By adopting this synthesis technique, it was also possible to control the dimension and the final shape of the nanoparticles. Several syntheses were carried out during the research work, modifying the molecular weight of the reducing agent and/or the firing temperature, in order to evaluate the influence such parameters have on the Ag-nanoparticles formation. The syntheses were monitored with the use of UV-Vis spectroscopy and the average dimension as well as the morphology of the nanoparticles was analysed by SEM. From the spectroscopic data obtained from each synthesis, a kinetic study was completed, relating the progress of the reaction to the two variables (ie temperature and molecular weight of the reducing agent). The aim was finding equations that allow the establishing of a relationship between the operating conditions during the synthesis and the characteristics of the final product. The next step was finding the best method of synthesis for the decorative application. For such a purpose the amount of nanoparticles, their average particle size, the shape and the agglomeration are considered. An aqueous suspension containing the nanoparticles is then sprayed over the fired ceramic tiles and they are subsequently thermally treated in conditions similar to the industrial one. The colorimetric parameters of the obtained ceramic tiles were studied and the method proved successful, giving the ceramic tiles stable and intense colours.

Constraints are widely present in the flight control problems: actuators saturations or flight envelope limitations are only some examples of that. The ability of Model Predictive Control (MPC) of dealing with the constraints joined with the increased computational power of modern calculators makes this approach attractive also for fast dynamics systems such as agile air vehicles. This PhD thesis presents the results, achieved at the Aerospace Engineering Department of the University of Bologna in collaboration with the Dutch National Aerospace Laboratories (NLR), concerning the development of a model predictive control system for small scale rotorcraft UAS. Several different predictive architectures have been evaluated and tested by means of simulation, as a result of this analysis the most promising one has been used to implement three different control systems: a Stability and Control Augmentation System, a trajectory tracking and a path following system. The systems have been compared with a corresponding baseline controller and showed several advantages in terms of performance, stability and robustness.