The modern trend of gas turbines design is towards lighter, highly efficient,and more compact engines. Such situation imposes on engineers to continuouslysearch for improved and optimum designs. The thesis presented aims at researching possible performance improvements regarding axial gapdistance in transonic compressors. Decreasing the axial gap would result inlighter engines and achieve design goals. The influence of decreasing the axialgap on performance and structure integrity should be throughly analyzed. This thesis work includes numerical investigations on the axial gap distance effect on performance efficiency and related unsteady aerodynamics phenomena. The first one and a half compressor stages of a Siemens Gas Turbine are modeled in ANSYS CFX. Different axial gap models are simulated for differentconfigurations. The steady state solution is obtained to be initialized for transient time marching calculations. Furthermore, the computational cost of transient calculations is reduced through a geometry scaling technique. The unsteady behavior is further analyzed by a Harmonic Balance solver implemented in STAR-CCM+ software, and compared to a reference case transient calculations. The results obtained supports the presence of an optimalaxial gap distance for maximum efficiency in transonic compressors. Further, the harmonic balance method shows good possibilities for cost and time reductions in transonic compressors performance calculations.

ABSTRACTThe purpose of this thesis is to design and analyze the new generation leading edge slat of a commercial jet to reduce the structural noise with the application of new conceptual design approaches. Recent scientific research show that the leading edge slats account for the structural noise during the flight operation therefore, when the leading edge slat is deployed under different flight conditions, an open gap/slot is formed between the high lift device and the wing box. However, since the leading edge slat includes flexible sections, it is assumed that defining an adaptive system inside the leading edge slat may reduce the structural noise by utilizing bending properties of these flexible sections. Hence, electromechanical actuator designing gains also great importance in the whole process. In this study, we have used, finite element modelling of the slat structure to examine the required structural deformations and strengths; our work is based on the software ANSYS/Workbench. To be realistic in deciding the right geometry in the follow up steps, we have first studied a generic geometry having no aerodynamics or actuator forces application. The whole simulation was performed by defining dummy forces and dummy material properties. The simulation lead to having a global overview of the mechanical behaviour of the structure; further, once the influent parameters were tested, realistic aerodynamic forces and material properties were defined, and as a result of bending of the flexible sections the required gap closure was formed between the trailing edge of the slat and the wing box. Subsequently, the suitable actuator design and required strength analysis are also performed on the last section. This study has also proved that the use of adaptive systems on the leading edge slats improves flight comfort by reducing the structural noise and provides less fuel consumption; this is significant for the long run considerations of aeroplane manufacturers. / es Zentrum für Luft- und Raumfahrt e. V. (DLR)

Den viktigaste aspekten av ett rum är onekligen den rymd det rymmer. Denna aspekt är osynlig, men hörbar. Det som syns är rummets ytor, det som hörs är rummets djup. Så det bästa sättet att utforska ett rum är kanske genom att lyssna snarare än att titta. Och tänk om musik, komponerad i ett utrymme, var lyktan som belyste dess rymd. Detta projekt, vid namn Det osynliga rummet, handlar om att undersöka relationen mellan rum, ljud och musik. Forskningsfrågorna är– på vilket sätt kan rummet bli en del av instrumentet och kompositionen? och – vad kan musiken berätta om rummet? För att undersöka detta använde jag en modulär, analog synthesizer, skapade och spelade in över åtta timmar minimalistisk och repetitiv musik i S:t Johannes kyrka i Malmö. Över en månads tid gjorde jag tolv besök i kyrkan och använde aktionsforskning som metod för att dokumentera och guida processen. Jag upptäckte att rummet är mycket mer än bara en förskönande effekt – det ger musiken rymd, filtrerar den och adderar liv genom ljudlandskapet, både från omgivningen och interiören. Men det är inte en enkelriktad relation – rummet och musiken ger båda varandra en adderad dimension av djup och musiken och ljudlandskapet färgar varandra. / The most important aspect of a room is arguably the space it contains. This aspect is invisible, but audible. What is seen is only the surfaces of a room, what is heard is its depths. So perhaps the best way to explore a space is by listening rather than looking. And what if music, composed in the room, were the torch with which the space was illuminated? This thesis project, called The invisible room, is centered around the relationship between sound, music and space. The questions are – in what way can the space become part of the instrument and the composition? And – what can the music say about the space? To research this I used a modular synthesizer, created and recorded over eight hours of minimalistic and repetitive music in S:t Johns church in Malmö. Over a months time I made twelve visits to the church, using the method of action research to document and guide the process. I found that the audible room is much more than just an embellishing effect – the space makes the music spacious, filters it and adds life through the soundscape, both from the surroundings and the interior of the room.  But it’s not a one way street – the space and the music both give each other an added dimension of depth and the soundscape and the music colors each other. / <p>Till arbetet hör 26 ljudbilagor som alla är smakprov från längre inspelingar.</p>

The EDEN ISS project, initiated by the German Aerospace Center (DLR) focuses on the development of greenhouses for future Space habitats on the Moon and Mars. For this, they run a full-size experiment in Antarctica in collaboration with NASA. This experiment is remotely controlled and monitored by the mission control team in Bremen, Germany. The aim of this thesis is to improve the accessibility of the data being pulled from the greenhouse in Antarctica and delivered to the mission control room. Furthermore, it promises to provide the EDEN ISS team with a set of tools to quickly and easily analyze historical data from the numerous sensors and devices currently installed inside the greenhouse module. To accomplish this, the development of a Data Analysis Tool was designed and programmed in Python, which generates accurate graphs and plots in a fast and user-friendly manner. This tool provides the user with a Graphical User Interface (GUI) which includes a set of easy-to-use tools to modify and manipulate the available data throughout the entire experiment’s lifetime, covering the years from 2018 to 2021. By using this tool, the EDEN ISS team can access relevant data and reach informed conclusions regarding the functionality and stability of the greenhouse experiment module in Antarctica.

Beyond Atlas is a Swedish private company with the goal of exploring the solar system with cheap and reliable spacecraft. Part of their maiden mission, Hugin, aims to demonstrate navigation, propulsion, and communication technology on a 3U CubeSat. This thesis aims to investigate the feasibility of using the Enpulsion NANO electric propulsion (EP) system for deep-space applications and how to best demonstrate its capabilities in low-Earth orbit. Literature reviews of scientific papers and software simulations were conducted to gain an understanding of the underlying processes involved in EP in-orbit operations. Analyses were made on orbital maneuvers, momentum unloading, power and thermal restrictions. The results suggest that the EP system's capabilities is mainly limited by the saturation time of the reaction wheels restricting longer duration orbital maneuvers. Orbital maneuvers for demonstrating the capabilities are proposed based on the limitations imposed on the EP system by the rest of the spacecraft. On the basis of the results of this research, it can be concluded that the Enpulsion NANO thruster's operational range can be utilized both as a low thrust efficient main drive and as a high thrust maneuvering thruster for deep-space applications but is limited by the high power consumption and low thrust-to-power ratio.

The aim of the thesis is to provide the mission requirements for the VEGA Transportation System(VTS), the equivalent of Phase 0 of a space project. The decrease in sizes and masses of the satellites opened the opportunity for the light capability VEGA launchers to contribute and reshape the European space value chain. VTS is envisaged to be an extension of the services offered by the VEGA launcher family, by providing solutions and services of space transportation and orbital exploitation. The elaboration of this thesis followed closely a methodology for defining complex space missions discussed by authors in “Methodology for requirements definition of complex space missions and system” and “Reusable space tug concept and mission”, which emphasizes the need of both, the Functional Analysis and Concept of Operation as fundamental activities to assess and derive the mission requirements. The results section reports a thorough description of the results obtained in the quest of identifying and characterizing new missions requirements for VTS. Specifically, missions for Releasing payload(s) to its/their final position and missions for Providing charter for In-Orbit Verification / In-Orbit Experimentation / In-Orbit Demonstration were exemplified. The mission requirements are summarized at the end of the section. A parallel between the findings and the current space trends is drawn in the Discussion, with details about the target market and how VTS could reshape it. A short discussion on how the entire portfolio of missions are amalgamated, in such a way that as few systems as possible can handle these missions is also provided. Lastly, a comparison between the work performed within the AVIO project and a sounding rocket project is given, providing thoughts about the lessons learned from both of them. Eventually, the conclusions are drawn based on the missions presented throughout thethesis and explains how the entire portfolio of missions will be further analyzed and more requirements will be deployed for the refinement of the entire VTS. / Syftet med denna rapport är att formulera uppdragskraven, motsvarande fas noll i ett rymdprojekt, för VEGA Transportation System (VTS). Minskningen i storlek och massa hos satelliter har öppnat upp för att VEGA, som är byggd för små nyttolaster, kan bidra till och utöka den europeiska uppskjutningskapaciteten och tjänsterna för olika rymdtransporter. Denna studien följer till stora delar metoderna som presenteras i “Methodology for requirements definition of complex space missions and system” samt “Reusable space tug concept and mission”. I dessa publikationer understryks behovet av både funktionell analys samt operationskonceptet som fundamentala aktiviteter för att bedöma och formulera uppdragskraven. Resultatavsnittet går igenom de framtagna uppdragkraven med de ovan nämnda metoderna. I diskussionsavsnittet analyseras nuvarande trender inom rymdsektorn och hur VTS kan vara med och forma utvecklingen samt den tänkta marknaden för systemet. Det diskuteras hur flera rymduppdrag kan slås ihop så att så få system som möligt kan hantera dessa uppdrag. Slutligen görs en jämförelse mellan arbetet inom AVIO-projektet med ett REXUS-sondraketprojekt, med tankar och lärdomar från båda projekten. Slutsatser dras utifrån portföljen av uppdrag som tagits fram för VTS i studien. VTS kommer framöver att fortsätta analyseras samt motiveras med flera argument för dess förbättring.

The aerodynamic performance of any airborne vehicle is an important characteristic to be considered during the concept development process. Lift and drag forces are the two most important aspects of aerodynamics that dictates vehicle efficiency. As these forces depend on various conditions, evaluating the performance at the intended flight condition is necessary. As the experimental investigations are extremely expensive, computational methods are used to find the performance characteristics of a vehicle in the early design stages. The main focus of this thesis is to find the aerodynamic parameters of an UAV, lift coefficient (Cl) and drag coefficient (Cd) at a predefined flight state and further investigate the trim performance in turn flight state. Two types of computational methods were used namely Panel Methods i.e., Vortex Lattice Method (VLM) and Computational Fluid Dynamics (CFD). These methods differ by computational time and accuracy. Investigations were performed to two UAV models namely UAV1 andUAV2 where both models have minor differences in design. Both VLM and CFDwere used to investigate the performance of UAV1. This was done to find the maximum capability of VLM, which is computationally cheaper. A trim analysis was also performed to find additional parameters to aid the comparison of VLM and CFD. Apart from investigating UAV1 at the required flight states, investigation was also performed at near stall to find the performance of UAV1 in worse flight condition. A comparison of UAV1 and UAV2 was then made to find the best flight states where an UAV can fly fulfilling the designer requirements. UAV2 was then simulated to find the trim condition of a level flight by deflecting the elevator control surfaces in turn flight state. The results from the analysis showed that VLM provides reasonable results within its limitations. From the CFD results, both the UAV’s have sufficient Cl, but the Cd of UAV1 is approximately twice the Cd of UAV2. The turn analysis of the UAV2 showed that at a higher angle of attack, UAV2 can bank at a large bankangle without losing the level flight condition.

The first European commercial research facility aboard the ISS, Space Applications Services' ICF, provides a platform for standardized plug-and-play experiments called ICE Cubes. The ICE Cubes Service provides engineering and operational support for ICE Cubes missions. In order to facilitate rapid and affordable access to space, a programmatic choice was made to mainly use COTS components in Cube design. As part of a company-internal project to develop a generic ICE Cubes platform for biological experiments, a scientific requirements document was drawn up in cooperation with interested scientists. A decision was made to aim for an experiment size of 2U (200x100x100mm). The main scientific requirements are to accommodate six reaction chambers (referred to as "wells") of standardized size; to control the temperature at well level to remain in the nominal interval of (37 +- 1)C; to accommodate a combined volume of 230ml of fluids; to provide capability to image each of the wells; and to allow for freezing of the biological payload to -80C for return to ground. The development of a prototype design for this platform, dubbed BioCube, is the topic of this thesis. Technical requirements were derived, and a functional breakdown was defined. From this, the system was partitioned into five subsystems: Thermal, Imaging/Avionics, Structure, Software, and the biological Payload. The development of the biological system is considered beyond the scope of this thesis, and the development of the software beyond that required for prototyping is left for a later stage in the design process, as significant heritage exists from previous experiments. Using a rapid prototyping approach, a prototype design for this experiment has been developed. The proposed solution utilizes a (205x104x101)mm outer structure, manufactured from aluminium and closed with two lids on the small faces. Inside, the system is split into a 3D printed avionics compartment and a payload compartment, surrounded by an air gap serving as thermal insulation. The payload compartment structure consists of aluminium, closed on one face with a transparent material through which the samples can be imaged, and provides a sealed interface connector for exchange of power and data. Both the outer structure and the payload compartment are sealed at the interfaces using O-ring seals, providing a combined two levels of biosafety containment to the payload. Manual latches on one of the lids of the outer structure allow it to be opened and the payload compartment to be extracted.The system avionics are based on a Raspberry Pi Zero with USB &amp; Ethernet Hub and Motor Control expansion boards. A 5W silicon heating pad attached to the inside of the payload compartment provides heating, and is controlled using a PWM signal from the motor control board.Two cameras arranged in parallel are used to image wells arranged in two rows, reducing the required motion. One axis motion is implemented using a leadscrew mechanism actuated by a DC motor, driven by the motor control board. Prototyping has been performed on nearly every part of the proposed design. The leadscrew assembly has been successfully tested, and tests on a thermal model have successfully demonstrated binary thermal control achieving the nominal temperature range. Some points regarding the design remain to be defined, and more thorough verification and validation of the design remains to be performed. / La première installation de recherche commerciale européenne à bord de l'ISS, l'ICF de Space Applications Services, fournit une plateforme pour des expériences standardisées prêtes à l'emploi appelées ICE Cubes. Le ICE Cubes Service fournit un soutien technique et opérationnel pour les missions ICE Cubes. Afin de faciliter un accès rapide et abordable à l'espace, un choix programmatique a été fait d'utiliser principalement les composants COTS dans la conception des expériences. Dans le cadre d'un projet interne à l'entreprise visant à développer une plateforme ICE Cubes générique pour les expériences biologiques, un document sur les exigences scientifiques a été rédigé en coopération avec les scientifiques intéressés et il a été décidé de viser une taille d'expérience de 2 U (200x100x100 mm). Les principales exigences scientifiques sont les suivantes : accueillir 6 chambres de réaction ("puits") de la taille des puits d'une plaque à 6 puits ; contrôler la température au niveau des puits pour qu'elle reste dans l'intervalle nominal de (37 +- 1)C ; accueillir un volume combiné de 230ml de fluides ; fournir la capacité d'imager chacun des puits; et permettre la congélation de la charge utile biologique à -80\,$^\circ$C pour le retour au sol. Le développement d'un prototype de plate-forme, baptisé BioCube, est le sujet de cette thèse. Les exigences techniques ont été dérivées, et un découpage fonctionnel a été défini. A partir de là, le système a été divisé en cinq sous-systèmes : Thermique, Imagerie/Avionique, Structure, Logiciel, et la charge utile biologique. Le développement du système biologique est considéré comme hors de portée de cette thèse, et le développement du logiciel au-delà de ce qui est nécessaire pour le prototypage est laissé pour une étape ultérieure dans le processus de conception, car il existe un héritage important des expériences précédentes. En utilisant une approche de prototypage rapide, une conception de prototype pour cette expérience a été développée. La solution proposée utilise une structure extérieure de (205x104x101)mm, fabriquée en aluminium et fermée par deux couvercles sur les petites faces. À l'intérieur, le système est divisé en un compartiment avionique imprimé en 3D et un compartiment de charge utile, entourés d'une lame d'air servant d'isolation thermique. Le compartiment de la charge utile est en aluminium, fermé sur une face par un matériau transparent, à travers lequel les échantillons peuvent être imagés, et fournit un connecteur d'interface scellé pour l'échange d'énergie et de données. La structure extérieure et le compartiment de la charge utile sont scellés aux interfaces à l'aide de joints toriques, offrant ainsi deux niveaux combinés de confinement de biosécurité à la charge utile. Des loquets manuels sur l'un des couvercles de la structure extérieure permettent de l'ouvrir et d'extraire le compartiment de la charge utile.L'avionique du système est basée sur un Raspberry Pi Zero avec des cartes d'extension USB &amp; Ethernet Hub et Motor Control.Un coussin chauffant en silicone de 5W fixé à l'intérieur du compartiment de la charge utile, assure le chauffage et est contrôlé par un signal PWM provenant de la carte de contrôle du moteur.Deux caméras disposées en parallèle sont utilisées pour imager les puits disposés sur deux rangées, ce qui réduit le mouvement nécessaire. Le mouvement sur un axe est réalisé à l'aide d'un mécanisme de vis sans fin actionné par un moteur à courant continu, piloté par la carte de commande du moteur. Le prototypage a été effectué sur presque toutes les parties de la conception proposée. L'assemblage de la vis sans fin a été testé avec succès, et les tests sur un modèle thermique ont démontré avec succès que le contrôle thermique binaire atteint la plage de température nominale. Certains points concernant la conception restent à définir, et une vérification et une validation plus approfondies de la conception restent à effectuer.

This paper will investigate the development of a landing footprint for a re-entry vehicle. Vehicles can re-enter the atmosphere with a range of orientations, velocities and flight path angles. The central question is whether a vehicle with any combination of these states can be brought to an acceptable landing condition at a particular landing site and with a particular landing speed. To aide in this investigation several models must be implemented, including that of the atmosphere, the vehicles, the Earth, and the aerodynamics. A detailed analysis of the aerodynamic model will be treated, and the equations of motion subject to these aerodynamic laws will then be compared to results from existing atmospheric reentry software. The principles of optimization will then be employed to generate the footprint of landable states, based on maximum and minimum possible downrange distances, for two vehicle concepts.

A study of the viabliness of a UAV for humanitarian relief missions has been done. With an aeronautical model fulfilling humanitarian logistics has then the manufacture and operational life-cycle costs as well as the present air jurisdiction. In contrast to this has also an evaluation of the empty weight conceptual estimation equation been reviewed and what conditions fairly describes the sizing of a UAV. The study finds there’s a technical possibility, economic plausibility but a need for legal development. The coefficients which are sufficient to estimate the empty weight ratio are the Home built aircrafts and powered sailplane. The study concludes what present off-the-shelf systems that might be suitable to sustain humanitarian relief missions. / Syftet med den här studien har varit att undersöka möjligheterna för att använda drönare till att leverera humanitär hjälp. Att ge humanitär hjälp innebär att man assisterar stater i att leverera nödvändiga varor och tjänster till områden där den nationella staten behöver assistans för att upprätthålla nödvändiga livsvillkor för befolkningen. Det kan vara att leverera mat och mediciner men även enklare skolmateriel eller liknande. Oftast är orsaken bakom en humanitär insats att det skett någon typ av katastrof, det kan vara både natur och mänskligt skapade katastrofer. Ett exempel på en sådan nylig kris har varit inbördeskriget som rasat i Syrien under större delen av 2010-talet. Ett problem som har dykt upp är att det är svårt att få fram rätt hjälp dit den behövs, speciellt om de civila som har behovet befinner sig i en krigszon. I ett sådant fall är det mycket riskabelt att transportera och leverera humanitär hjälp till de som behöver det. De riskerar att bli skjutna, kidnappade och kapade. Detta skapar både personliga och materiella skador. Frågan blir då om man skulle kunna leverera den hjälpen med drönare, för att minska risken för personskador men också minska effekten för hela hjälpinsatsen om en eller flera av drönare skulle förvinna. Det som komplicerar hela i logistiken är att man måste ta hänsyn till hur personer byter besittning av godsen och hur man verifierar att varje person får just rätt hjälp. Speciellt då värdet av godset i en kris kan bli asymptotiskt högt. För att testa huruvida det är möjligt att använda UAV:er för humanitär hjälp skapades en simuleringsmodell av en drönare. Eftersom det förväntades att ett uppdrag är ungefär 300 km + 300km tur-o-retur övergavs någon typ av helikopterdesign tidigt. Modellen simulerade många uppdrag som bedömdes vara relevanta för en UAV som skulle leverera humanitär hjälp. Utifrån dessa uppdrag bedömdes några av de operativa kostnader som var knutna till uppdragen. Det gäller främst tillverkningskostnader, bränslekostnader samt avgifter som behöver betalas av den som använder luftrummet. Det finns en bok som är flygplanskonstruktörens bibel (Aircraft Design). Den är skriven av Daniel P. Raymer. Han föreslår där en formel för hur man konceptuellt kan bestämma vikten av ett nytt flygplan. De befintliga planen jämfördes sedan med formeln för att undersöka om dessa också stämde på drönare. Eftersom drönare inte har piloter ombord innebär det att vissa apparater inte behöver finnas på det flygplanet, vilket kan tänkas ändra hur mycket en UAV estimeras väga jämfört med ett vanligt plan. Studien kommer fram till att det som Raymer har föreslagit verkar för det mesta vara rättvisande även när man designar UAV:er. Avslutningsvis identifieras tre olika drönare som med mer eller mindre modifiering skulle kunna användas för humanitära insatser. Dock är, som nämnt tidigare, de flesta UAV:er utvecklade för olika typer av informationssamling. Då flera av dessa apparater inte är lika nödvändiga i en humanitär-logistisk situation är det sannolikt att inköpspriset skulle vara billigare än annars. Slutsatserna är att det nu är tekniskt möjligt att använda drönare för humanitär hjälp, ekonomiskt är det möjligt om än dyrt men juridiskt är det i dagsläget inte möjligt. Juridiken och reglementet för hur avgiftssystemet och luftrummet fungerar behöver utvecklas för att på ett hållbart och säkert sätt integrera autonoma farkoster med befintlig luftfart. Beroende på hur regleringarna av luftrummet förändras, ändras även de ekonomiska förutsättningarna för att använda drönare för att utföra logistiska uppdrag.