This master’s thesis is aimed to examine the possible range increase of a ballistically fying body equipped with a propeller working at transonic velocities. To determine whetherthe propeller will provide an improvement in range, results from simulations are compared to corresponding cases of similar bodies fying without a propeller. Different airfoil geometries were examined using the computer software Fluent. Thereafter, a geometry was created from scratch based on wing and propeller theory and was simulated on using the computer software ICFD++ which, may be used for computational fuid dynamics. According to the simulations the increase in range was shown to be 3-4% further for the specifc projectile chosen for this work. For the furthest fying cases the initial velocity of the body was higher than what the propeller had been optimized for, and regions of supersonic velocities developed on the geometry. This did however not impose any substantial impediments according to the simulations, although a field test would likely have displayed stalling and following, a worsening of performance. / Detta examensarbete syftar att undersöka räckviddspåverkan på en annars ballistiskt flygande kropp vars bakparti försatts med en propeller färdandes i transsoniska hastigheter. För att bedöma huruvida detta kan vara till nytta, ställs resultatet från simuleringar med propeller upp mot resultatet för motsvarande fall utan propeller. En geometri har skapats med grund i ving-och propellerteori och därefter har simuleringar utförts i mjukvaran ICFD++, som används till beräkningar av strömningsmekanik. Avseende räckviddspåverkan visade simulationerna på en ökning av räckvidden på drygt 3-4% längre avstånd för den specifka projektil som hade valts att simulera på. För de längre fallen gällde dock en högre utskjutningshastighet än vad propellern var väl anpassad för och områden av överljudshastigheter utvecklades på geometrin. Detta visade ingen betydlig påverkan i simulationerna men verkliga tester hade sannolikt visat på överstegring och med det en försämrad prestanda.

The Lite (Light) satellite for the study of B-mode polarization and Inflation from cosmic background Radiation Detection (LiteBIRD) is a Japan Aerospace Exploration Agency (JAXA)-led Strategic Large-Class mission designed to search for the existence of the primordial gravitational waves produced during the inflationary phase of the early Universe, through the measurement of their imprint onto the polarization of the Cosmic Microwave Background (CMB). It is an international collaboration, with European Union (EU) operations being coordinated by France. A short study on the merits of 2-dimensional versus 3-dimensional elements in the Finite Element Model (FEM) meshing of basic plates and beams was performed as well as the analysis of two different methods of representing threaded connections in FEM models. Both these activities were in service of the creation of a FEM model of the structure of the contribution of the EU to LiteBIRD: the Medium-High-Frequency Telescope (MHFT). All analysis was done using the Siemens NX software and the Simcenter Nastran solver. This model has passed preliminary quality checks and will be used for future structural analysis intended to verify the integrity of the design, its compliance with JAXA requirements, and to perform screw dimensioning. The results of those analyses will inform possible future design changes or will support the current design. Logistical work on the project was also performed, consisting of the groundwork to initiate an Assembly, Integration and Testing (AIT) plan and an Assembly, Integration and Verification (AIV) plan. This primarily involved the creation of a Model Definition Document, which contained clear and complete descriptions of the different MHFT models to be used throughout project development. The document defines the purpose and components of the models, the dependencies between models, as well as the necessary tests to be performed on each as part of the AIT and AIV process. A list of the structure interfaces was also created, which will contribute to the development of an interface control document.

The Swedish Sea Rescue Services (SRSS) has developed an Unmanned ArialVehicle (UAV) which they use for search and rescue missions. The SRSS wantsto upgrade this UAV to also be able to fly and drop with a package. Bydesigning according to the model of designing by HH van den Kroonenberg [2].The main functions for the package is that it needs to be able to carry at least 300gram and be 900x900x25 millimetres big. After designing 3 concepts, one mainconcept is chosen and produced as a Solidworks model. This package and thejoint to hold the package have been designed and have been calculated to be ableto withstand the stresses during flight. The stresses include the weight of thepackage as well as the aerodynamic drag. With a safety factor of 1.5. Also afinite element simulation is done to check the main stresses, this simulationshows that the critical beam will not be able to hold. It is recommended that amore dense EPP is used or the beam will be redesigned. Also an engineerspecialized in aerodynamics is recommended to take a look at the results to befully secure.

This report summarizes the task of conceptually designing an UAV suited for agricultural observation of Swedish farmland. The design of the UAV was divided into two parts. This report focuses on the flight mechanics, performance analysis, and cost analysis of the UAV, whereas the other part centers around the aerodynamic performance. Therefore, some elements, such as the wing selection, will not be subject to discussion in this report. A set of different requirements were posed, such as having a flight time longer than two hours, being able to between 5-10 m/s, able to perform vertical take-off and landing, fly at a maximum of 100 meters, and weighing less than 5 kg. By using different sources of literature, reasonable assumptions, and Matlab analytics, a UAV was designed that met all constraints demanded. The cost analysis yielded a result that was reasonable, which overall makes this conceptual UAV a realistic product that could be manufactured using the project design.

Using autonomous underwater vehicles is a popular method of collecting samplesand conducting surveys, but the transportation of this information is not always easy.The underwater vehicle might be unable to transmit the information wirelessly, andsamples may be required to be transported a long distance. A possible solution tothese problems is a hybrid unmanned aerial vehicle, accompanying said underwatervehicle. After a submerged deployment, this vehicle could transport the informationover long distances, or conduct other operations at different locations in air or water.While quadcopters are an increasingly popular type of vehicle, conventional fixed­wingplanes are still superior when it comes to range. This thesis designs, builds and testssuch a vehicle, with the goal of a submerged deployment, performing vertical takeoff,and then transitioning to fixed­wing flight. To minimize the drone’s impact on thevehicle which it accompanies, it is nearly buoyancy neutral by flooding the hull withwater, which enters and exits the vehicle rapidly during dive and egress. To managethe pressure at the underwater vehicle’s operating depth, it utilizes a bladder ratherthan having a heavy rigid compartment. It floats as a tailsitter at the surface, usingtwo motors in a tractor configuration to pull itself out of the water. The vehicle builtproved capable of being submerged and taking off vertically, however there were nofixed­wing flights attempted. / Autonoma undervattensfordon är en populär metod för att samla in prover ochgöra undersökningar, men det är inte alltid uppenbart hur denna informationska transporteras. Undervattensfarkosten kanske inte har kapaciteten att sändainformationen trådlöst, och prover kan krävas att transporteras en lång sträcka. Enmöjlig lösning på dessa problem är en hybrid obemannad flygande farkost som följermed undervattensfordonet. Efter en undervattensstart kan detta fordon transporterainformationen över långa avstånd, alternativt genomföra andra operationer på olikaplatser. Quadcoptrar är en alltmer populär typ av fordon, men konventionella flygplanär fortfarande överlägsna när det gäller räckvidd. Denna avhandling konstruerar,bygger och testar ett sådant fordon, med målet att efter en undervattenstart, genomföravertikal start från vattenytan och sedan övergå till horisontell flygning. För attminimera drönarens inverkan på fordonet som den transporteras med har den nästanneutral flytkraft, detta sker genom att kroppen fylls med vatten, som snabbt kommerin och ut ur fordonet under dykning och vid flygning. För att hantera trycket påundervattensfordonets operationsdjup använder den en blåsa i stället för att ha enstyv behållare. Den flyter med svansen ner på ytan, och använder två motorer ien traktorkonfiguration för att dra sig ur vattnet. Fordonet som byggts visade sigkunna sänkas ned under vattnet och lyfta vertikalt, men det gjordes inga horisontellaflygningar.

Vacuum arc thrusters offer a relatively simple and cheap form of satellite propulsion, especially suitable for nanosatellites such as CubeSats or even smaller. This thesis focuses on vacuum arc thruster design considering the thruster’s manufacturing, assembly and integration into the spacecraft, and proposes a new anode geometry easing thruster production. Vacuum arc thruster research is traditionally experimental in nature due to a lack of accurate models. This work follows this approach, and studies experimentally the effect of several geometric design parameters on thruster performance. The outcome confrms findings from several papers, and suggests specifc improvements towards existing models for predicting the effect of the thruster’s geometry on its thrust. The chosen experimental approach raised the need for a micro-thrust measurement stand. Two distinct measurement stands have been designed, realized and used to test various thruster prototypes. One test stand is more accurate. However, the other setup allows for considerably faster testing.

The goal of this thesis is to create the phase A design for IceBrain-1's power subsystem. The mission in itself is an AI powered image recognition test platform that will be used to see how much information is needed for an AI to detect different objects from space. To accomplish this the satellite will use two computers to run different algorithms. These are big power consumers and therefore it is important to have a power subsystem that can supply that power and energy. To create this design the platform and its components needed to be selected. To fit the IceBrain-1 payload the 16u platform from GOMSpace has been chosen and thus most components will be from that supplier. To get the power consumption and generation of the satellite, orbital simulations were done in the program 42 whose data was then used in larger simulations in matlab. Where two scenarios were created with different assumptions regarding power usage. The findings of this thesis suggest that the power subsystem is heavily dependant on the runtime of the AI computers. A longer duty cycle will require more batteries for them to fulfil the requirement set by this thesis. More solar panels might also be needed for the satellites end of life. The thesis ends with two proposals for the setup of the satellites power subsystem depending on which of the two scenarios is closer to reality. / Målet med denna uppsats är att skapa en fas A design för IceBrain-1s kraftpaket. Satelliten är en AI driven bildigenkännings-testplattform som ska användas för att se hur mycket information det krävs för att en AI ska kunna identifiera objekt från rymden. För att utföra detta kommer satelliten använda sig utav två datorer som kör olika algoritmer. Dessa har en relativt hög energikonsumtion och kräver därför ett kraftpaket som kan leverera den energin. Designen utgår ifrån GOMSpaces 16u kubsatellitplattform och använder främst komponenter från deras utbud i mån det finns. För att generera data på hur mycket energi som används och genereras så utfördes omloppsbanesimulationer i programmet 42. Datan från den användes sedan i ytterliggare simulationer inuti Matlab där två olika scenarier med olika antaganden hade skapats. Resultatet från arbetet är att kraven på kraftpaketet är till största del baserat på hur länge datorerna kör. Om de är igång en längre tid kommer det att krävas mer batterier för att uppfylla kraven tillsammans med mer eller större solpaneler kan också krävas vid slutet av dess livstid. Två olika kombinationer av solpaneler och batterier kan användas av satelliten baserat på om vilken av de två scenarierna som är närmre verkligheten. / IceBrain-1

Sounding rockets and small suborbital payloads provide a means for research in situ of the atmosphere and ionosphere. The trajectory and the attitude of the payload are critical for the evaluation of the scientific measurements and experiments. The trajectory refers the location of the measurement, while the attitude determines the orientation of the sensors. This thesis covers methods of trajectory and attitude reconstruction implemented in several experiments with small suborbital payloads carried out by the Department of Space and Plasma Physics in 2012--2016. The problem of trajectory reconstruction based on raw GPS data was studied for small suborbital payloads. It was formulated as a global least squares optimization problem. The method was applied to flight data of two suborbital payloads of the RAIN REXUS experiment. Positions and velocities were obtained with high accuracy. Based on the trajectory reconstruction technique, atmospheric densities, temperatures, and horizontal wind speeds below 80 km were obtained using rigid free falling spheres of the LEEWAVES experiment. Comparison with independent data indicates that the results are reliable for densities below 70 km, temperatures below 50 km, and wind speeds below 45 km. Attitude reconstruction of suborbital payloads from yaw-pitch-roll Euler angles was studied. The Euler angles were established by two methods: a global optimization method and an Unscented Kalman Filter (UKF) technique. The comparison of the results shows that the global optimization method provides a more accurate fit to the observations than the UKF. Improving the results of the falling sphere experiments requires understanding of the attitude motion of the sphere. An analytical consideration was developed for a free falling and axisymmetric sphere under aerodynamic torques. The motion can generally be defined as a superposition of precession and nutation. These motion phenomena were modeled numerically and compared to flight data. / <p>QC 20170510</p>

This degree project studies the future regulations for the installation of electronic flight bags (EFB) with focus on the hardware and its safety implications in which the task was given by Bromma Air Maintenance (BAM). The aim is to ease the operator to handle issues dealing with EFB; such as lithium battery fire in the cockpit, placement of EFB in the cockpit, etc. This also addresses flight safety, flight controls, emergency evacuation and solutions in dealing with such issues. Flight safely is a vital factor to be considered since it jeopardizes lives. As recent reports indicate an increase in lithium battery powered devices incidents on aircrafts, this paves the way to find new solutions and procedures to mitigate them. By studying the current regulations, Acceptable Means of Compliance (AMC), Advisory Circular (AC) regarding the usage/installation of EFB and future regulation draft (NPA) this study analyzed the changes, which indicated that there were not many significant changes made to the future regulation (new AMC). Although many chapter of the current AMC have been removed and introduced into a new section under AMC &amp; GM (Guidance Material). Different placement of the EFB in cockpit has also been studied in this degree project, which has shown that depending on the placement choice of the aircraft operator there are advantages and disadvantages. This follows by studying the lithium (Li-ion) batteries: technology, mitigation of fire and procedures for lithium battery fire while also studying the recent incidents regarding lithium batteries fire and explosion in commercial and cargo flights. The solutions consist of using the latest technology to propose a new approach to charge the batteries, and store the burning batteries as well. This lead to a smart inductive charger and a smart fire contamination bag to be integrated into the procedures. / Detta examensarbete studerar de framtida installationskrav för Electronic Flight Bag (EFB) med fokus på hårdvaran och dess påverkan på säkerheten. Rapporten kan användas som manual som tydliggör vilka procedurer och rekommendationer operatören kan ta hänsyn till vid installation och användning av EFB. I flygbranschen har de flesta flygbolag redan börjat använda surfplattor istället för dokument och manualer. EFB är ett elektroniskdisplaysystem som i första hand används i flygplanets cockpit. EFB:s funktion är att förse piloten med en mängd olika data om flygplanet t.ex. prestanda, balans och vikt beräkningar, bränsle mm. Displayen är en ersättning av det traditionella ”Flight Bag” som för i tiden var i pappersform och innehöll alla kartor och manualer skriftligt. Som alla andra teknologier har EFB sina begränsningar såsom batteriproblem, påverkan på säkerheten och ”Flight Controls” i flygplanets cockpit. Genom studier och sammanfattning av skillnaden mellan nuvarande och framtida regelverk har man kommit fram till att inga märkbara förändringar har skett. Fältstudien var till nytta för att analysera vilka säkerhetsproblem varje installationstyp har. Utrustningar som smart induktiv laddare och smart brandskyddsväska har fåtts som resultat i arbetet. Dessa utrustningar är till att motverka faror som är möjliga att ske under användning av EFB i cockpit.

When building aircrafts, structural components must be designed for high strength, low cost, and easy assembly.To meet these conditions structural components are often based upon previous designs, even if a new component is developed.Refining previous designs can be a good way of preserving knowledge but can also limit the exploration of new design concepts. Currently the design process for structural aircraft components at SAAB is managed by design engineers. The design engineer is responsible for ensuring the design meets requirements from several different disciplines such as structural analysis, manufacturing, tool design, and assembly.Therefore, the design engineer needs to have good communication with all disciplines and an effective flow of information. The previous design is refined, it is then reviewed and approved by adjacent disciplines.Reviewing designs is an iterative process, and when several disciplines are involved it quickly becomes time consuming.Any time the design is altered it has to be reviewed once more by all disciplines to ensure the change is acceptable.So there is a need for further customizing the design concept to decrease the number of iterations when reviewing. Design Space Exploration DSE is a well known method to explore design alternatives before implementation and is used to find new concepts.This thesis investigates if DSE can be used to facilitate the design process of structural aircraft components and if it can support the flow of information between different disciplines.To find a suitable discipline to connect with design a prestudy is conducted, investigating what information affect structural design and how it is managed.The information flow is concluded in a schematic diagram where structural analysis is chosen as additional discipline. By using topology optimization in a DSE, design and structural analysis are connected.The design space can be explored with regards to structural constraints.The thesis highlights the possibilities of using DSE with topology optimization for developing structural components and proposes a method for including it in the design process.