A drop tower is a device that produces a microgravity environment by allowing an experiment to free fall for a short period of time, usually less than 10 seconds. Certain types of drop towers are also capable of reproducing the gravitational conditions of other celestial bodies, such as Lunar and Martian gravity. Microgravity environments are often required for many different scientific experiments, such as experiments in material science, fluid dynamics, biological studies and many other fields. Microgravity environments are also often used as a specialized manufacturing method for certain materials. Components and systems that will be used in space or onboard sounding rockets can also be tested and verified using drop towers before launch. There is an ever-present need to conduct experiments in a microgravity environment and thus highlights the importance and relevance of drop towers in research and design verification. Other microgravity facilities such as sounding rockets, parabolic flights and orbital spacecraft typically provide longer microgravity durations, however, come at a considerable cost. This highlights the need for drop towers that are cost-effective as a desirable research device. This thesis consists of a comprehensive, systematic literature review to determine industry standards and the current state of the art in the world of drop towers. The different potential mechanical designs of a drop tower are then analyzed and trade-offs are completed. The most suitable design, that could feasibly be built at Luleå University of Technology (LTU)’s space campus, is chosen and presented later in this thesis. The safety of the drop tower was of utmost concern when deciding on the most suitable design as well as when completing the mechanical design of the drop tower. The slider is a major component of a drop tower, it houses the experiment and is a critical component in determining the achievable microgravity quality. The slider design was also analyzed with a trade-off analysis of the potential existing designs, with the most feasible design being chosen. The drop tower is planned to be installed in the LTU Spacecampus light garden which can accommodate a drop tower of approximately 13m in height. The mechanical design is verified using various Finite Element Analysis (FEA) simulations. The 14m planned and designed drop tower is a non-vacuum, guided design which would provide approximately 3 seconds of microgravity, 5.2 seconds of Martian simulated gravity and 7.8 seconds of Lunar simulated gravity. The drop tower has been designed to accommodate projects that are part of the REXUS program. The towers' considerable size and ease of use would make it suitable for many research institutions and many potential scientific studies.

A space cadet wakes up by the rattle of his spaceship leaving the atmosphere of the earth. He is faced with the glowing sphere of his destination, the Moon, ahead of him. As he approaches the point where he is supposed to launch the rocket for course trajectory, he ponders his life, his village, and his education. But he needs to maintain his focus - if he launches the rocket too late, he will have passed the gravity field of the moon, and will be lost in space forever. / [I examensarbetet ingår utställningen "There is Plenty of Misery for Everyone":] Lentikulärbilder med 3d effekt samt animation av groteska motiv som har kopplingar till holländskt 1600tals måleri Material: Lentikulärbilder i plastram. Teknik: Foto/video. / <p>Examensarbetet består av 9 bilder samt en essä</p>

SAAB saknade en skriven arbetsmetod för att tillvarata enheter och komponenter från avionik som antingen ska kasseras eller klassas som oreparerbart. Syftet med detta arbete var att ta fram en gemensam metod i form av en handbok för de anställda på SAAB. Denna handbok ska underlätta när arbetsmoment gällande tillvaratagande ska utföras och skapa enhetlighet kring metod och dokumentering. Även en undersökning av de regelverk SAAB måste följa för att bedriva underhåll av militär avionik genomfördes för att se till att handboken följer de bestämmelser som finns. Tillsammans med handboken så skapades även ett flödesschema som ska underlätta arbetsgången vid tillvaratagande. Slutligen så undersöktes hur tillvaratagande påverkar en organisations underhållsarbete, vad för slags fördelar samt nackdelar det finns med att använda tillvaratagna  enheter/komponenter och när man bör och inte bör använda sig av tillvaratagande. Dessa resultat togs fram genom litteraturstudier. Arbetet resulterade med en handbok samt ett flödesschema som anställda på SAAB ska kunna använda vid arbeten med tillvaratagande, där förklaras hur arbetsförloppet ska gå till och att det görs på korrekt sätt enligt de regelverk som SAAB måste följa. Arbetet tog även fram för- och nackdelar med tillvaratagande av avionik samt i vilka fall när man bör och inte bör tillvarata elektroniska komponenter från avionik som ska kasseras eller klassas oreparerbart. / At SAAB, there was an absence of an adequate working written method on the reuse of devices and components from avionics that should either be discarded or classified as unrepairable. The aim of this thesis was to develop an established method in the form of a handbook for the SAAB employees. The manual will facilitate the execution of work-related tasks and create consistency regarding methodology and documentation. A survey on the regulations that SAAB must abide to conduct maintenance of military avionics was executed in order to ensure that the handbook complies with all the provisions that exist. A flow chart was created alongside the handbook for the purpose of aiding the workflow. Ultimately the provisions’ affect upon the organization’s maintenance work was examined, such as the advantages and disadvantages for reusing consumed units/components and whether one should or should not reuse units/components. These results were obtained by means of literary studies.  The project resulted with a handbook and a flowchart that SAAB employees can use in their procurement work in which it explains the work methods and work process in order to ensure that it is completed correctly and according to the rules that SAAB has to follow. The project additionally highlighted the strengths and weaknesses of the utilization of reused units/components, and also when one should and should not reuse electronical components from avionics that are either being discarded or classified as unrepairable.

A novel continuous low-thrust fuel-efficient model predictive control strategy for multi-satellite formations flying in low earth orbit is presented. State prediction relies on a full nonlinear relative motion model, based on quasi-nonsingular relative orbital elements, including earth oblateness effects and, through state augmentation, differential drag. The optimal control problem is specically designed to incorporate latest theoretical results concerning maneuver optimality in the state-space, yielding to a sensible total delta-V reduction, while assuring feasibility and stability though imposition of a Lyapunov constraint. The controller is particularly suitable for networked architectures since it exploits the predictive strategy and the dynamics knowledge to provide robustness against feedback losses and delays. The Networked MPC is validated through real missions simulation scenarios using a high-fidelity orbital propagator which accounts for high-order geopotential, solar radiation pressure, atmospheric drag and third-body effects.

Cube Satellite (CubeSat) launches have been on the rise since its first launch in2003. This popularity is mainly due to faster design process and lower launch costs.However, most CubeSats are launched into Low Earth Orbits (LEOs), with nomissions to Geostationary Transfer Orbits (GTOs). However, many mission areplanned for the next half-decade.A major challenge to launch a CubeSat into a GTO is the thermal environmentof the higher altitude orbits. These orbits are significantly colder due to reducedheating from Earth’s planetary and albedo radiations, and a possibility for longereclipses due to the eccentricities of GTOs.A thermal investigation of the thermal environment was done using the Foresailmissions as examples, as the missions currently are set to fly the first missions toPolar LEO. The trajectories for the second Foresail mission are being evaluated,with the GTO being a strong contender. This thermal investigation is done througha comparative study of the two missions. The thermal effects of a few missionspecific scenarios were also evaluated.This provided a holistic thermal design of the first Foresail mission. A region specificthermal solution for the battery was analyzed. The various mission scenarios andtheir comparisons with the LEO mission, also formed a basis of the feasibility ofvarious situations on the second mission. Moreover, the results, in part assessedthe thermally feasibility to launch a 3U CubeSat into a GTO.The results showed GTOs show larger magnitude of variation of thermal loads ascompared to LEOs. However, these variations are more gradual due to the largerorbital periods. A 3U CubeSat can be launched into both, the LEO and GTOenvironments with passive thermal control. The properties of the thermal coatsvary slightly. However, it is not possible to passively control the CubeSat if theeclipse occurred at the aphelion of the orbit.

The road transport industry is facing a strong need for fuel consumption reduction, driven by the necessity of decreasing polluting emissions, such as CO2 and NOX, as well as coping with strict regulations and increasing fuel costs. For road vehicles the aerodynamic drag constitutes a major source of energy consumption, and for this reason improving the aerodynamic performance of the vehicle is an established approach for reducing fuel consumption and greenhouse gases emissions. In this Thesis work, Computational Fluid Dynamics (CFD) investigations have been carried out in order to investigate and improve the aerodynamic performance of an unloaded timber truck. The work has been divided in two parts. In a first phase, a preliminary study was carried out on a simplified tractor-trailer model in order to establish a suitable computational grid and turbulence model. The hexcore-mesh showed a better performance over the tet- and poly-mesh types. Among the selected RANS turbulence models, the Realizable k − ε with Enhanced Wall Treatment (EWT) and y+ &gt; 30 showed the highest reliability of results in comparison with experimental data and existing CFD investigations. In a second phase, the flow field around the baseline unloaded timber truck was analysed in order to highlight potential regions for drag reduction. The truck cabin-bulkhead gap, bunks, the exposed wheels and the stakes were found make key contribution to the drag build-up. The analysis confirmed the 5◦-yaw case to be the most representative for the wind-averaged drag coefficient. Geometry modifications were implemented in order to improve the aerodynamic performance in the selected areas, and subsequently combined into aero-kits in order to enhance the performance, analysed for the 5◦-yaw case. The combination of extended side skirts, bulkhead shield and collapsed stakes yielded a remarkable result of more than 30% decrease in the wind-averaged drag coefficient, achieved by reducing the flow separation on the cabin leeward A-pillar, and by shielding areas of high stagnation pressure from the side wind. Furthermore, a parallel study was conducted on the development of a procedure for the automatic post-processing of results. The outcome was a set of Python scripts to be used with Kitaware Paraview in order to automatically obtain figures of surface variables distributions, iso-surfaces, velocity profiles, drag build-up and total pressure contours. The procedure was finally extended to include the case comparison. / ETTaero2

No description available.

This Master Thesis work cover the simulation of the movement of charged species exposed to a high gradient electric field, the same environment a plasma actuator produces. The final goal is to use the plasma actuator as an active flow control device to decrease the drag of a body moving in air. This report describes how the problem was set up in COMSOL Multiphysics and the resulting volume force achieved. The volume force is the force generated by the plasma actuator that is acting on the air. To understand the effect of a plasma actuator better experimental work was also performed. The experimental work include what effect a plasma actuator has on a wing that has stalled out and measuring the air velocity obtained from a single plasma actuator. The conclusion is that more work has to be performed to make the plasma actuator a more effective flow control device. This type of work is a way to understand how plasma actuators work and in extension will lead to how a plasma actuator will be used effectively. / Detta examensarbete behandlar simuleringen om hur laddade partiklar rör sig när de utsätts för ett elektriskt fält med hög gradient, ett liknande närområde som skapas av en plasma aktuator. Slutmålet är att kunna använda plasma aktuatorer som en aktiv flödeskontroll med avsikt att minimera motsåndet på en stelkropp som rör sig genom luften. Den här rapporten beskriver hur problemet ställs upp i COMSOL Multiphysics och vilken volymkraft som fås utav simulerignen. Volymkraften är den genererade kraft från plasma aktuatorn som aggerar på den omgivande luften. Utöver simuleringen har praktiska experiment gjorts för att förstå effekten från en plasma aktuator bättre. Dessa experiment består av hur en plasma aktuator förändrar luftströmmen över en vinge som redan tappat sin lyftkraft och av att mäta vilken hastighet luften kan nå på grund av en plasma aktuator. Sammanfattnignen är att mer arbete behöver göras för att effektivisera en plasma aktuator om den ska användas för flödeskontrol. Detta arbeta är ett steg i att förstå hur plasma aktuatorer fungerar vilket i förlängningen kommer leda till hur man ska använda en plasma aktuator på bästa sätt.

The Perpetual Environmental Station (PES1), designed and developed is robust, modularenvironmental station with a multitude of sensors, to study the precursors of Earthquakes and todisseminate a long term, quality data of various atmospheric parameters. The PES1 has beendesigned based on the Earthquake precursors, postulated in various research articles. Most ofthese postulated precursors have been tested in laboratory environments and PES1 will be thefirst station to validate these precursors on field. The PES1 has been designed from a modularpoint of view, considering perpetuity where modules can be easily added, replaced, or upgradedsuch that a long-term functioning of the system is guaranteed. The PES1 will be installed inIceland where the seismic activity is quite high, serving as an ideal test location.The thesis work outlines the precursors of Earthquakes and the seismicity in Iceland, where thePES1 is to be installed. The design and development of the PES1 is described from the hardwareand software point of view, with specifications of each sensor used in the Environmental Station.

The subject of the thesis is analysis and modeling of the entry, transport, and atmospheric precipitation of solar wind ions, H+ and He2+, into the induced magnetosphere of Mars. The solar wind is a flow of charged particles emitted by the Sun. The solar wind carries with it a magnetic field, the interplanetary magnetic field (IMF). The IMF piles up on the dayside of the non-magnetized Mars and is then convected towards the nightside. The solar wind ions can normally not cross the magnetic barrier, formed by the pile up IMF. However, in situ observations by the Mars Express spacecraft reveal that downward moving solar wind H+ and He2+ are sometimes present in the Martian ionosphere, below the magnetic barrier. The gyroradii of shocked solar wind ions may be comparable to the size of the dayside Martian magnetic barrier and for certain circumstances, these ions can gyrate through. Observations by Mars Express are used to analyze H+ and He2+ penetrating through the magnetic barrier and precipitating into the Martian ionosphere, identified by the presence of ionospheric photo-electrons. A case study shows evidence of narrower energy distributions for H+ (with energy ≥ solar wind energy), as the spacecraft moves down in altitude. From this, the study concludes that the magnetic barrier prevents the lower energy H+, from reaching low altitudes. The thesis also describes a statistical study of precipitating H+ fluxes, which indicate that H+ precipitation is rare (detected during 3% of the dayside observation time only) and carries on average 0.2% of the upstream solar wind particle flux. In another statistical study, the thesis shows that the precipitation of H+ and He2+ decreases even further when Mars encounters solar wind pressure pulses. A possible explanation is that the enhanced mass loading of the magnetic field flux tubes by planetary heavy ions, while the tubes drag through the ionosphere at lower altitudes, slows down their velocity and allows more magnetic flux to pile up. The magnetic barrier becomes a more effective obstacle to the solar wind ion precipitation. Furthermore, the thesis describes a model of H+ precipitation onto the Martian upper atmosphere using a hybrid code of the Mars solar wind interaction. The spatial patterns of the precipitation depend on the H+ energy, on the H+ origin (solar wind or generated from the hydrogen corona) and on the altitude. Some features of the observed H+ distributions are reproduced by simulations, while others are not, indicating a more complex physics than in the model. The thesis also describes amodel study of transport of H+, fast H atoms and He2+ through the atmosphere using a Direct Simulation Monte Carlo model. This study demonstrates the crucial role of the magnetic field in determining the energy deposition of the solar wind ions in the topside atmosphere. For instance, a horizontal magnetic field with strength of 50 nT backscattered almost all H+, thus preventing these particles to deposit their energy at lower altitudes. The conclusion of the thesis work is that although some solar wind ions do precipitate, the magnetic barrier effectively protects the onospherefrom precipitating solar wind ions. / Ämnet för avhandlingen är analys och modellering av inflödet av solvindsjoner, H+ och He2+, genom Mars inducerade magnetosfär. Solvinden är ett flöde av laddade partiklar från Solen. Solvinden bär med sig ett magnetfält, det så kallade interplanetära magnetfältet (IMF). IMF packas ihop framför dagsidan av planeten innan det tar sig vidare mot nattsidan. Solvindsjoner kan vanligtvis inte passera denna magnetiska barriär som skapas då IMF packas ihop. Dock avslöjar in situ-observationer av rymdsonden Mars Express att nedåtflödande H+ och He2+ från solvinden ibland påträffas inuti Mars jonosfär, nedanför den magnetiska barriären. Gyroradierna hos solvindsjoner i shockregionen kan vara jämförbara med storleken av den magnetiska barriären over Mars dagsida och i vissa fall kan jonerna gyrera igenom barriären. Observationer från Mars Express används för att analysera H+ och He2+ som tar sig igenom den magnetiska barriären och ner i Mars jonosfär, vilken identifieras genom närvaron av jonosfäriska fotoelektroner. En fallstudie visar tecken på smalare energifördelningar av H+ (med energi ≥ solvindens energi), ju lägre rymdsonden tog sig. Från detta slutleder studien att den magnetiska barriären reflekterar H+ med lägre energi och förhindrar dem från att nå lägre altituder. Avhandlingen beskiver även en statistisk studie av inflödande H+, vilken indikerar att inflödet av H+ är sällsynt (observeras enbart under 3% av observationstiden över dagsidan) och bär i genomsnitt med sig 0.2% av partikelflödet som finns uppströms i solvinden. I en annan statistisk studie visar avhandlingen att inflödet av solvindsjonerna H+ och He2+ minskar ytterligare när Mars möter tryckpulser i solvinden. En möjlig förklaring är att den ökade masslastningen av magnetfältets av tunga planetära joner, då magnetfältet släpas genom jonosfären på lägre höjd, bromsar upp magnetfältet och orsakar ytterligare hoppackning av magnetfältet. Det gör den magnetiska barriären till ett mer effektivt hinder för inflödet av solvindsjoner. Vidare beskriver avhandlingen en modell för inflöde av H+ till Mars övre atmosfär genom att använda en hybridkod för Mars växelverkan med solvinden. Mönster i utbredningen av inflödet beror på energin hos H+, på källan till H+ (solvinden eller skapad från vätekoronan), och på altituden. Vissa egenskaper hos H+-fördelningarna återskapas av simuleringar, medan andra inte gör det, vilket tyder på en mer komplicerad fysik än i modellen. Avhandlingen beskriver också en modellstudie av transport av H+ , snabba H atomer, och He2+ genom atmosfären med en Direct Simulation Monte Carlo modell. Denna studie demonstrerar den avgörande roll som magnetfältet har i att bestämma energin som solvindsjoner avlämnar i den övre atmosfären. Till exempel reflekterade ett horisontellt magnetfält på 50 nT nästan allt H+, och förhindrade dessa partiklar från att avlämna sin energi på lägre altituder. Slutsatsen av avhandlingen är att även om vissa solvindsjoner tar sig igenom, så är den magnetiska barriären ett effektivt skydd av jonosfären mot infallande solvindsjoner. / <p>Godkänd; 2012; 20121009 (catdiv); DISPUTATION Ämne: Rymdteknik/Space Technology Opponent: PhD Christian Mazelle, Institut de Recherche en Astrophysique et Planétologie, Toulouse, France Ordförande: Professor Stas Barabash, Svenska institutet för rymdfysik, Kiruna Tid: Fredag den 14 december 2012, kl 10.00 Plats: Aula, Svenska institutet för rymdfysik, Kiruna</p>