Additive Manufacturing (AM, 3D printing) has made significant advancements over the past decade and has become a viable alternative to traditional machining techniques. AM offers several advantages over traditional manufacturing techniques including improved geometric freedom, reduction in part lead time, cost savings, enhanced customization, mass reduction, part elimination, and remote production. There are many different AM processes with the most commonly used process being Fused Filament Fabrication (FFF). Small satellites have also made significant advancements over the past two decades with the number of missions launched annually increased by orders of magnitude over that time span. Small satellites offer several advantages compared to traditional spacecraft architectures including increased access to space, lower development costs, and disaggregated architectures. On-orbit manufacturing and assembly have become major research and development topics for government and commercial entities seeking the capability to build very large structures in space. AM is well suited on-orbit manufacturing since the process is highly automated, produces little material waste, and allows for a large degree of geometric freedom. This dissertation seeks to address three major research objectives regarding applications of additive manufacturing in space systems: demonstrate the feasibility of 3D printing an ESPA class satellite using FFF, develop a FFF 3D printer that is capable of operating in high vacuum and characterize its performance, and analyze the coupled dynamics between a satellite and a robot arm used for 3D printing in-space. This dissertation presents the design, finite element analysis, dynamic testing, and model correlation of AdditiveSat, an additively manufactured small satellite fabricated using FFF. This dissertation also presents the design, analysis, and test results for a passively cooled FFF 3D printer capable of manufacturing parts out of engineering grade thermoplastics in the vacuum of space. Finally, this dissertation presents a numerical model of a free-flying small satellite with an attached robotic arm assembly to simulate 3D printing structures on-orbit with analysis of the satellite controls required to control the dynamics of the highly coupled system. / Doctor of Philosophy / 3D printing has made significant advancements over the past decade and has become common place in offices, schools, and even the homes of hobbyist. 3D printing has become an alternative to traditional machining techniques, such as machining parts from blocks of material. 3D printing offers several advantages over traditional manufacturing techniques including improved geometry freedom, reduction in part lead time, cost savings, enhanced customization, mass reduction, part elimination, and remote production. There are many different types of 3D printing with the most commonly used process being Fused Filament Fabrication (FFF) in which a thermoplastic is melded by a hotend and then extruded through a nozzle to deposited material layer-by-layer onto a printed part. Small satellites have also made significant advancements over the past two decades with the number of missions launched annually greatly increased over that time span. Small satellites offer several advantages compared to traditional spacecraft including increased access to space and lower development costs. On-orbit manufacturing and assembly have become major research and development topics for government and commercial entities seeking the capability to build very large structures in space. This dissertation seeks to address three major research objectives regarding applications of additive manufacturing in space systems: demonstrate the feasibility of 3D printing an ESPA class satellite using FFF, develop a FFF 3D printer that is capable of operating in high vacuum and characterize its performance, and analyze the coupled dynamics between a satellite and a robot arm used for 3D printing in-space. This dissertation presents the design, analysis, and test results of AdditiveSat, a 3D printed small satellite made using FFF. This dissertation also presents the development of a FFF 3D printer capable of operating in the vacuum of space. Finally, this dissertation presents a numerical simulation that models 3D printing structures on-orbit with a small satellite equipped with a robot arm.

Vacuum-assisted toilets make use of a large pressure difference between the ambient pressure and a vacuum tank to transport waste from the toilet bowl to the septic tank. This process requires 98% less water per flush making it an attractive product for transport vehicles such as airplanes, cruise ships, and trains. Unfortunately, the water savings come at the cost of high noise levels. This thesis investigates the acoustic characteristics of a vacuum-assisted toilet flush and several methods to reduce the radiated noise. Some methods include changing rinse parameters such as rinse pressure, rinse length, and rinse timing, adding structural damping of the bowl to reduce re-radiation, inserting a tube between the bowl and valve that utilizes a larger bend radius and longer tube length than what is currently installed, and modifying the valve. The most effective solution without requiring more water per flush was to insert a tube. The initial peak level was reduced by 16 dB and the steady-vacuum noise was reduced by 5 dB. Evidence of evanescent decay and reduced flow velocity as possible mechanisms for the noise reduction are presented and discussed. Rinse variations show a strong impact of the rinse-tube interaction on the noise reduction. In addition to these techniques, a modified flush plate opening and closing velocity profile is suggested which optimizes the sound generated by the opening and closing of the valve. Finally, a promising dual-valve solution that may take extra coordination of vacuum-assisted toilet manufacturers and airplane/cruise ship/train manufacturers is presented. By placing a secondary valve near the septic tank, the main noise from the valve is significantly reduced.

[ES] Hyperloop es considerado el quinto medio de transporte, después del coche, barco, tren y avión. Consiste en una capsula de levitación magnética que viaja dentro de un tubo en el que la presión de aire ha sido reducida. Entonces, la fricción con el suelo y resistencia aerodinámica son minimizadas, alcanzando ultra altas velocidades a nivel de tierra. Actualmente hay en desarrollo varios trenes maglev y conceptos hyperloop. La mayoría proponen levitar usando Suspensión Electromagnética (EMS). Zeleros, la compañía donde esta Tesis ha sido realizada, tiene una propuesta similar. Zeleros usa un EMS Híbrido (HEMS), combinando imanes y electroimanes para reducir los requerimientos de energía. Respecto a la propulsión, la propuesta es única ya que hace uso de un compresor de la industria aeroespacial. Simulaciones CFD prueban que usar un compresor reduce considerablemente la resistencia aerodinámica en el ambiente cerrado, ya que el efecto pistón es mitigado. Para el mismo tamaño de tubo y presión, un hyperloop con compresor requiere hasta 70 % menos potencia. En otros términos, si la misma potencia es instalada en el vehículo, el diámetro de la infraestructura puede ser 2.8 veces más pequeño. Esta Tesis desarrolla un simulador 0D para evaluar el rendimiento de la solución hyperloop propuesta. Resolver su aerodinámica requiere solucionar un fujo interno y externo de Fanno. El último combina efectos de Couette y Poisuille en un dominio anular. Así, se desarrolla un modelo simplificado para flujos de Fanno, acelerando así el modelado básico. Esta aproximación matemática incluye información de la velocidad de la pared y de la forma del dominio, evitando integrar un sistema de EDOs. La solución tiene una desviación en la ratio de presiones de 5 % respecto a CFD, y del 10 % en la longitud crítica. El simulador modela toda la termodinámica del vehículo, incluyendo el compresor, conductos, turbina, tobera y flujo externo. Este modelado es similar al del ciclo de Bryton, sin cámara de combustión. Además, se incluye un modelo para predecir la masa y longitud de la cápsula y sus componentes. Así, las pérdidas de fricción y requerimientos de potencia y energía son obtenidos. Estos resultados presentan una desviación máxima del 20 % respecto a CFD. Además, un proceso de optimización para encontrar la solución más eficiente se ha desarrollado con el código, para vehículos de 50 y 150 pasajeros. Se ha encontrado que es más beneficioso absorber menos gasto másico con el compresor, ya que la energía requerida para comprimir el flujo interno es más alta que las pérdidas en el canal externo. Comparando el consumo de energía específico de esta solución con otros medios de transporte, el hyperloop se encuentra cercano al rendimiento de los maglev. Éste es, también, entre tres y cinco veces más eficiente que los aviones. Además, es más competitivo que el avión en términos de velocidad media en una ruta hasta los 800 km. Por último, se desarrolla un modelo similar para un sistema de escala media. Este prototipo, cuya velocidad objetivo es de 500 km/h, es diseñado por Zeleros previo al sistema de escala real. Su simulador incluye además los efectos transitorios y la termodinámica del tubo, asumiendo una velocidad del sonido infinita. Gracias a este código, se puede obtener el rendimiento en una misión. Inicialmente, el prototipo incrementa la presión del tubo aguas arriba, y la reduce aguas abajo debido al efecto pistón, generando una velocidad inducida. Al final de la misión, el flujo puede ser transferido otra vez, y las presiones se equilibran otra vez. Este modelo también predice el par y potencia del motor eléctrico, además de los parámetros de la batería (voltaje, corriente y profundidad de descarga). / [CA] Hyperloop és considerat el cinquè mitjà de transport, després del cotxe, vaixell, tren i avió. Consisteix en una càpsula de levitació magnètica que viatja dins d'un tub on la pressió d'aire es reduïda. Aleshores, la fricció amb el sòl i resistència aerodinàmica són minimitzades, aconseguint ultra altes velocitats a nivell de terra. Actualment hi ha en desenvolupament diversos trens maglev i conceptes hyperloop. La majoria proposen levitar usant Suspensió Electromagnètica (EMS). Zeleros, la companyia on aquesta Tesi ha sigut realitzada, té una proposta similar. En particular, el concepte de Zeleros utilitza un EMS Híbrid (HEMS), combinant imants i electroimants per reduir els requeriments d'energia. Pel que fa a la propulsió, la proposta és única, ja que fa ús d'un compressor de la indústria aeroespacial. Simulacions CFD proven que utilitzar un compressor redueix considerablement la resistència aerodinàmica en un ambient tancat, ja que l'efecte pistó és mitigat. Per a la mateixa grandària de tub i pressió, un hyperloop amb compressor requereix fins a 70 % menys potència. En altres termes, si la mateixa potència és instal·lada al vehicle, el diàmetre de la infraestructura pot ser 2.8 vegades més menut. Aquesta Tesi desenvolupa un simulador 0D per avaluar el rendiment de la solució hyperloop proposada. Resoldre l'aerodinàmica del hyperloop requereix solucionar un flux intern i extern de Fanno. L'últim combina efectes de Couette i Poiseuille en un domini anular. Així, es desenvolupa un model simplificat per a fluxos de Fanno, accelerant així el modelatge bàsic. Aquesta aproximació matemàtica inclou informació de la velocitat de la paret i de la forma del domini, evitant integrar un sistema de EDOs. La solució té una desviació a la ràtio de pressions de 5 % respecte a CFD, i del 10 % a la longitud crítica. El simulador modela tota la termodinàmica del vehicle, incloent-hi el compressor, conductes, turbina, tovera i flux extern. Aquest modelat es similar al del cicle de Bryton, sense càmera de combustió. A més, s'inclou un model per predir la massa i la longitud de la càpsula i els seus components. Així, les pèrdues de fricció i requeriments de potència i energia són obtinguts. Aquests resultats presenten una desviació màxima del 20 % comparat amb CFD. A més, un procés d'optimització per trobar la solució més eficient ha estat desenvolupat amb el codi, per a vehicles de 50 i 150 passatgers. S'ha trobat que és més beneficiós absorbir menys massa amb el compressor, ja que l'energia requerida per comprimir el flux intern és més alta que les pèrdues al canal extern. Comparant el consum d'energia específic d'aquesta solució amb altres mitjans de transport, el hyperloop és proper al rendiment dels maglev. Aquest també és entre tres i cinc vegades més eficient que els avions. A més, és més competitiu en termes de velocitat mitjana en una ruta fins a 800 km. Finalment, es desenvolupa un model semblant per a un sistema d'escala mitjana. Aquest prototip, la velocitat objectiu del qual és de 500 km/h, és dissenyat per Zeleros previ al sistema d'escala real. El seu simulador inclou a més els efectes transitoris i la termodinàmica del tub, assumint una velocitat del so infinita. Gràcies a aquest codi, es pot obtenir el rendiment en una missió. Inicialment, el prototip incrementa la pressió del tub aigües amunt, i la redueix aigües avall degut a l'efecte pistó, generant una velocitat induïda. Al final de la missió, el flux pot ser transferit una altra vegada, i les pressions s'equilibren una altra vegada. Aquest model també prediu el parell i potència del motor elèctric, a més dels paràmetres de la bateria (voltatge, corrent i profunditat de descàrrega). / [EN] Hyperloop is considered the fifth means of transportation, after the car, boat, train and plane. It consists of a magnetically levitating capsule that travels within a tube in which the air pressure has been reduced. Thus, the ground friction and aerodynamic drag are minimised, reaching ultra high-speeds at ground level. Several maglev trains and hyperloop concepts being developed currently. Most of them propose levitating using Electromagnetic Suspension (EMS). Zeleros, the company where this Thesis was done, has a similar approach. It employs a Hybrid EMS (HEMS)In particular, the Zeleros approach employs a Hybrid EMS (HEMS), combining permanent and electromagnets to reduce energy requirements. As for the propulsion, the approach is unique as it uses a compressor from the aeronautical industry. CFD simulations prove that using a compressor considerably reduces the aerodynamic drag in the closed environment, as the piston effect gets mitigated. For the same tube size and pressure, a hyperloop with compressor requires up to 70 % less power. In other terms, if the same power is installed on the vehicle, the infrastructure diameter can be 2.8 times smaller. This Thesis develops a 0D simulator to evaluate the performance of the proposed hyperloop solution. Solving the aerodynamics of the hyperloop requires solving internal and external Fanno flows. For the latter, the flow combines Couette and Poiseuille effects in an annular domain. Thus, a simplified model for Fanno flows is developed to accelerate the basic modelling. This mathematical approach includes the information of the wall speed and the shape of the domain, avoiding integrating an ODE system. The solution has a deviation in the pressure ratio of 5 % and 10 % in the critical length regarding CFD. The simulator models all the vehicle thermodynamics, including the compressor, duct, turbine, nozzle, and external flow. This modelling is similar to a Bryton cycle, without a combustion chamber. Also, a model to predict the mass and length of the capsule and its components is included. Thus, the friction losses and the energy and power requirements can be extracted. These outputs are compared with CFD results, with a maximum deviation of 20 %. Moreover, an optimisation process is conducted with the code to find the most efficient solution for 50- and 150-passenger vehicles. It is found that shallowing less mass flow with the compressor is better, as the energy required to compress the internal flow is higher than the losses on the external channel. Comparing the specific energy consumption of this solution with other means of transportation, the hyperloop is close to the maglev performance. It is also between three and five times more efficient than aeroplanes. Furthermore, the hyperloop is more competitive than the plane in terms of average speed on a route, up to 800 km. The last part of this work develops a similar model for a middle-scale system. This prototype, which aims to reach 500 km/h, is being designed by Zeleros before the real-scale one. Its simulator also includes the transient effects and the tube thermodynamics, assuming an infinite sound speed. Thanks to this code, the performance in a mission is obtained. The prototype initially increases the upstream tube pressure and reduces the downstream one due to the piston effect, generating an induced speed. At the end of the mission, the flow can be transferred again, and the pressures equilibrate again. This model also predicts the electric motor torque and power and the battery parameters (voltage, current, and deep of discharge). / Este trabajo ha recibido una subvención parcial del Ministerio de Ciencia, Innovación y Universidades bajo la ayuda “Doctorandos Industriales” número DI-17-09616. / Lluesma Rodríguez, F. (2022). Design and Optimisation of a Virtual Prototype of a Ground Transportation System at Very High-Speeds in Conditions Close to Vacuum [Tesis doctoral]. Universitat Politècnica de València. https://doi.org/10.4995/Thesis/10251/191409

This thesis explores the potential of utilizing metal-based plasma sources as a sustainable solution for high-powered electric propulsion and its implications for future interplanetary travel. Focusing on the Vacuum Arc Thruster and the Variable Specific Impulse Magnetoplasma Rocket engine, the study encompasses numerical simulations, analytical comparisons, and performance analyses to assess the feasibility of metal plasma fuels in space missions.The numerical analysis employs COMSOL Multiphysics to delve into the magnetohydrodynamics behavior within the VAT. Such simulation setup could provide valuable insights. Although the numerical results are disappointing for this paper, there exist possibilities within future work. The main hurdle is the simulation of vacuum. There are workarounds in COMSOL's Vacuum System Modeling tool which was not available for this thesis. Also, the used material properties were not suited for this high temperature plasma environment. The lack of material properties is a consequence of the insufficient research in the metal plasma field.Performance analysis is conducted on both the VAT and VASIMR engine, exploring efficiency, thrust capabilities, and feasibility for interplanetary missions. The results demonstrate the potential of metal-based plasma sources to reduce dependence on Earth for refueling and decrease mission costs. It is found that aluminum and magnesium have similar performance as the argon gas used in the VASIMR.Although challenges exist, such as integration problems and availability of material properties for metals in plasma states, the study underscores the promise of metal plasma fuels for sustainable space exploration. By advancing high-powered electric propulsion technologies, we move closer to realizing humanity's ambitious journey to distant celestial bodies. This research paves the way for future innovations, enabling a more self-sustaining space economy and unlocking new horizons of interplanetary travel.

Hybride Metall-Halogen Perowskit basierte Solarzellen haben im letzten Jahrzehnt eine noch nie dagewesene Entwicklung hinsichtlich ihrer Effizienzsteigerung erzielt. Dies ging mit einem rapiden Anstieg des Interesses der Forschungsgemeinschaft einher. Ein wichtiger Faktor für die Realisierung von Forschungsergebnissen ist der Übergang von Laborskalen zu industriellen Dimensionen, was grundlegende Anpassungen im Herstellungsprozess notwenig macht. Hier hat sich die physikalische Gasphasenabscheidung für andere Materialklassen bereits als gute Lösung bei der Herstellung von qualitativ hochwertigen Dünnschichten erwiesen. In dieser Arbeit wird die Vakuumabscheidung von FA₁ ₋ ₓCsₓPbI₃ ₋ ₓBrₓ für die Anwendung in Solarzellen durch Dreiquellenkoverdampfung erforscht. Durch eine Kombination aus optischen und Röntgen-basierten Messverfahren konnte eine Veränderung der Aufnahme des organischen Halogensalzes, Formamidiniumiodid (FAI), in die Perowkitverbindung in Abhängigkeit vom Kammerdruck festgestellt werden. Dadurch tritt eine Stöchiometrieänderung auf, welche sich in einer Bandlückenverschiebung niederschlägt. Außerdem wurde eine Veränderung der Kristallitorientierung beobachtet. Diese Ergebnisse motivieren eine genauere Untersuchung des Verdampfungsverhaltens des organischen Halogensalzes. Mit Hilfe von Massenspektrometriemessungen und einer detaillierten Erfassung der Prozessparameter konnte eine Zersetzung von FAI während der Verdampfung festgestellt werden. Desweiteren wurden weitere Besonderheiten im Abscheideverhalten, wie zum Beispiel Verdampfunsgrenzen und Veränderungen des Toolingfaktors beobachtet. Die Ergebnisse leisten einen wesentlichen Beitrag zum tieferen Verständnis der Vakuumabscheidung von organischinorganischen Metall-Halogen Perowskiten.:Kurzfassung iv Abstract v List of publications vi 1. Introduction 1 2. Theoretical background 5 2.1. Basics of thin-_lm solar cells . . . . . . . . . . . . . . . . . . . . . . . . . 5 2.2. Status of current thin-_lm solar cell technologies . . . . . . . . . . . . 7 2.3. The Perovskite system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2.4. Organic-inorganic mixed-halide metal perovskites . . . . . . . . . . . 14 2.5. Deposition methods of metal halide perovskite . . . . . . . . . . . . . 18 2.6. Vacuum deposition of perovskite . . . . . . . . . . . . . . . . . . . . . . 21 3. Experimental methods 27 3.1. Physical vapor deposition . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 3.2. Vacuum deposition of perovskite layers . . . . . . . . . . . . . . . . . . 29 3.3. Analytical techniques . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 4. Pressure dependent triple-source co-evaporation of methylammoniumfree perovskite 39 4.1. Precursor puri_cation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 4.2. Film deposition procedure . . . . . . . . . . . . . . . . . . . . . . . . . . 42 4.3. Crystallographic characterisation . . . . . . . . . . . . . . . . . . . . . . 43 4.4. Optical characterisation . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 4.5. Incorporation of FAI into thin-_lms . . . . . . . . . . . . . . . . . . . . . 50 4.6. Photovoltaic devices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 4.7. Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 5. Evaporation properties of formamidinium iodide 57 5.1. Degradation reactions of formamidinium iodide . . . . . . . . . . . . 57 5.2. Evaporation behaviour of formamidinium iodide . . . . . . . . . . . . 58 5.3. Theoretical considerations during the deposition process . . . . . . 61 5.4. Tooling behaviour of Formamidinium iodide . . . . . . . . . . . . . . . 63 5.5. Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68 6. Summary & Outlook 71 A. Appendix 75 List of Figures 81 List of Tables 82 List of Abbreviations 86 Bibliography 86 / In the last decade, hybrid metal halide perovskite-based solar cells have enjoyed an unprecedented surge in development within the research community. The next steps to further improve this technology will involve the transition from the laboratory to commercial-scale production, which will require adjustments in their fabrication processes. Here, physical vapour deposition has proven to be a good option for the fabrication of high-quality thin films for perovskites and other materials, like organic semiconductors. In this work, triple-source co-evaporation deposition of FA₁ ₋ ₓCsₓPbI₃ ₋ ₓBrₓ for the production of thin films for solar cell applications is investigated. With a combination of optical and X-ray-based measurement methods, a decrease in the incorporation of the organic halide salt formamidinium iodide (FAI) was found with increasing background pressure. This decrease results in a change in stoichiometry of the compound and, with it, a shift of the band gap. Furthermore, a change in crystallite orientation was observed. These findings motivate the examination of the evaporation behaviour of formamidinium iodide in more detail. With mass spectrometry measurements and detailed tracking of the process parameters, a degradation of FAI during evaporation was found. Furthermore, several effects of the deposition behaviour, evaporation limits, and tooling shifts were observed. These findings will be substantial for the deeper understanding of vacuum deposition of organic-inorganic metal halide perovskites, and will be significant in the expansion of perovskite-based solar technology.:Kurzfassung iv Abstract v List of publications vi 1. Introduction 1 2. Theoretical background 5 2.1. Basics of thin-_lm solar cells . . . . . . . . . . . . . . . . . . . . . . . . . 5 2.2. Status of current thin-_lm solar cell technologies . . . . . . . . . . . . 7 2.3. The Perovskite system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2.4. Organic-inorganic mixed-halide metal perovskites . . . . . . . . . . . 14 2.5. Deposition methods of metal halide perovskite . . . . . . . . . . . . . 18 2.6. Vacuum deposition of perovskite . . . . . . . . . . . . . . . . . . . . . . 21 3. Experimental methods 27 3.1. Physical vapor deposition . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 3.2. Vacuum deposition of perovskite layers . . . . . . . . . . . . . . . . . . 29 3.3. Analytical techniques . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 4. Pressure dependent triple-source co-evaporation of methylammoniumfree perovskite 39 4.1. Precursor puri_cation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 4.2. Film deposition procedure . . . . . . . . . . . . . . . . . . . . . . . . . . 42 4.3. Crystallographic characterisation . . . . . . . . . . . . . . . . . . . . . . 43 4.4. Optical characterisation . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 4.5. Incorporation of FAI into thin-_lms . . . . . . . . . . . . . . . . . . . . . 50 4.6. Photovoltaic devices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 4.7. Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 5. Evaporation properties of formamidinium iodide 57 5.1. Degradation reactions of formamidinium iodide . . . . . . . . . . . . 57 5.2. Evaporation behaviour of formamidinium iodide . . . . . . . . . . . . 58 5.3. Theoretical considerations during the deposition process . . . . . . 61 5.4. Tooling behaviour of Formamidinium iodide . . . . . . . . . . . . . . . 63 5.5. Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68 6. Summary & Outlook 71 A. Appendix 75 List of Figures 81 List of Tables 82 List of Abbreviations 86 Bibliography 86

No description available.

No description available.

Stockholm lies at the top in Europe in terms of population growth. It is growing from 30,000 to 40,000 residents each year and therefor puts high demands on the regions development. One of the governments reactions to this housing problem was to approve a bill that would simplify the regulatory framework in the planning and building act. It will among other permit owners of a one-or two family houses to build a 25  compliment housing without a building permit, so called attefallshus. In this final project, a small 25  house is designed. The house was designed to have thin exterior walls to maximize the indoor living space and also to fulfill all the Boverkets regulations for permanent housing. Vacuum Insulated panels were used as an insulation material in the envelope to achieve the extra thin exterior walls to maximize the living space. Various different simulations were done to simulate: Heat- and moisture transfer through the exterior walls, thermal bridges, energy calculations and the daylight factor inside the house. Additional calculations were done in Excel to compare the mean U-value calculated in simulations. The moisture transfer simulation did show that there should not be any moisture problems in the exterior walls. The mean U-value calculations in Excel and in the simulations showed values less than the limitations of Boverkets building regulations.

As advanced nozzles may offer alternative solutions to conventional nozzles for the future class of reusable launch vehicles, a critical aspect is to tailor these novel technologies to current recovery strategies, more specifically to vertical landing sustained by retro-propulsion. Researchers at Technische Universität Dresden have developed a dedicated test-bench for the vacuum wind tunnel facility, where Advanced Nozzle Concepts (ANCs), such as aerospike and dual-bell nozzles, are tested in cold-gas configuration while invested by subsonic counter-flows. The main objective of the test campaign is to evaluate the performance and altitude–compensation characteristics of such ANCs by simulating a vertical landing manoeuvre through the variation of ambient pressure experienced during the landing burn. A detailed description of design and development of the test-bench, together with preliminary results from the commissioning activities, are here offered to the reader. The force measurements, together with pressure and temperature data, contribute to evaluate thrust levels and coefficients, as well as the monitoring of the interaction between the nozzle cold-flow and the opposing free-stream. A background-oriented schlieren system allows to visualise the external flow-field. In conclusion, an outline of the upcoming test campaign and a description of the expected results is offered.

This project analyzes the relationship between military occupations and power vacuums. Specifically, it seeks to understand why some military occupations result in power vacuums while others do not. Pundits and policymakers have written extensively about the possibilities that the end of US occupations might yield dangerous power vacuums. These vacuums would create regional turmoil by inviting hostile actors and causing state failure. Based on these assumptions, many commentators caution against the withdrawal of forces. But what exactly is fearful about a power vacuum remains unclear. The concept of a power vacuum lacks defined parameters and scope, and why military occupations might lead to power vacuums is unknown. Much of the current analysis derives from familiar and recent cases of occupations of Iraq and Afghanistan. David Edelstein has the most comprehensive work on military occupations, but his work does not directly address the outcome of power vacuums. This project uses a mix multimethod research design to examine which factors cause power vacuums to emerge following occupations. It uses a comprehensive dataset of occupations since 1943. It will begin with a medium-n QCA and then proceed with case studies. The ultimate goal is to identify the conditions likely to lead to power vacuums and develop policy recommendations about how to avoid them. This project theorizes that a high level of economic destruction inflicted by the occupying military is a necessary condition for the absence of a power vacuum in the occupied territory. Shortened, this project calls this theory total destruction equals total buy-in. High levels of economic destruction inflicted by the occupier pacify the occupied population, while simultaneously delegitimizing the occupied state's previous regime. High economic destruction, which is defined as the decline of a state's per-capita GDP and overall population, is not the sole factor in preventing a power vacuum. Combinations of other conditions help influence the advent or absence of a power vacuum, but economic destruction inflicted by the occupier is the only condition that must be present in order to prevent a power vacuum. / Doctor of Philosophy / This project examines how, when, and why power vacuums emerge at the end of military occupations. Power vacuums evoke fear from pundits and policymakers, as hostile actors can exploit power vacuums to sow instability. Yet there remains no clear definition of what constitutes a power vacuums or substantive research on their etiology and impact. Policy discussions typically look to recent US experience in Iraq and Afghanistan to evaluate how the end of military engagement and occupation can create power vacuums. Thus risk of a power vacuum is often cited as justification to prolong military operations. To rectify this, this project will complete a replication and extension using David Edelstein's seminal dataset on military occupations. The dataset includes well-known cases such as the Allied occupations of Western Germany and Japan and lesser-known occupations like the Vietnamese occupation of Cambodia. Using a combination of within-case process tracing and Qualitative Comparative Analysis (QCA), the project seeks to elucidate what combination of conditions generate power vacuums following military occupations. The theory this project argues is that a high level of economic destruction inflicted by the occupying military is a necessary condition for the absence of a power vacuum in the occupied territory. The crux of this theory is that occupiers that engage in protracted conflict, inflicting widespread damage on a state before occupying it, are more likely to prevent a power vacuum from occurring. This widespread damage creates "breathing space" for the occupier to establish indigenous security forces (ISF) and a friendly government without having to worry about nationalist resistance from the occupied population.