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Dissertationen zum Thema „Rocker system“
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St, Germain Brad David. „Technique for the optimization of the powerhead configuration and performance of liquid rocket engines“. Diss., Georgia Institute of Technology, 2003. http://hdl.handle.net/1853/13063.
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Jansson, Albert, und Andreas Lezdins. „Student Rocket Experiment B2D2 - Power System“. Thesis, KTH, Skolan för elektroteknik och datavetenskap (EECS), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-293893.
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The B2D2 student experiment aims to study theEarth magnetic field by releasing a free falling unit (FFU) from asounding rocket. The power system of the FFU needs to supply allsubsystems with sufficient power and energy during the flight.This is achieved with two lithium cells and voltage regulatorsthat produce the required voltages and can deliver the necessarycurrent. The voltage regulators are tested on prototype PCBsand their performance evaluated. An attitude determination andcontrol system is needed to stabilise the FFU after release. Motordrive systems are custom designed for this purpose. The powerconsumption of the FFU is computer-simulated based on mea-surements on existing hardware. According to tests conducted,switching regulator designs with inductors are the best candidatesfor the power system. The chosen designs have sufficient marginsin current capacity to power the experiment during the durationof the mission with the chosen battery cells.Målet med studentexperimentet B2D2 är att studera det jordmagnetiska fältet genom att släppa en experimentmodul från en sondraket. Strömförsörjningssystemet i experimentmodulen behöver kunna leverera tillräcklig strömstyrka och energi till alla delsystem under experimentets varaktighet. Detta åstadkoms med två litiumceller och spänningsomvandlare som producerar de spänningar som behövs vid den strömstyrka som krävs. Spänningsomvandlarna testas på prototypkort för att utvärdera deras prestanda. Ett attitydkontrollsystem behövs för att stabilisera experimentenheten efter dess att den släppts. Till detta attitydkontrollsystem utvecklas ett motordrivsystem. Strömförbrukningen av experimentenheten simulerades utifrån mätningar på existerande hårdvara. Utifrån utförda tester bedöms de induktorbaserade switchande spänningsomvandlarna vara de lämpligaste. De valda kretsdesignerna har tillräcklig strömkapacitetsmarginal för att kunna strömförsörja experimentenheten under experimentets varaktighet med de valda battericellerna.
Kandidatexjobb i elektroteknik 2020, KTH, Stockholm
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Mockensturm, Jeffrey J. „Modernization of the Multiple Launch Rocket System embedded system software“. Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA295248.
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Bidgol, Saman, und Viktor Granberg. „Power supply system for the ISAAC rocket experiment“. Thesis, KTH, Skolan för elektro- och systemteknik (EES), 2013. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-199333.
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Kitchen, Seth, und Daniel Klinger. „TELEMETRY SYSTEM FOR INTERCOLLEGIATE ROCKET ENGINEERING COMPETITION VEHICLE“. International Foundation for Telemetering, 2017. http://hdl.handle.net/10150/626955.
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This paper describes a telemetry system for a high-powered rocket entered in the Intercollegiate Rocket Engineering Competition hosted by the Experimental Sounding Rocket Association. On-board the rocket GPS coordinates,acceleration, magnetic field and lux readings are collected,along with other data. The data is sent between internal systems using commercial Internet-of-Things boards that utilize IEEE 802.11 wireless protocols. The aggregated data is transmitted to a ground station through a monopole transmitting antenna and custom designed helical receiving antenna such that in the event of a crash, data is not lost. The ground station data recovery is performed using a commercial XBee transceiver, before being displayed in real time for tracking and safety purposes,and stored for future data analysis. The target apogee is 9 km, so real time GPS data will be useful for both tracking and vehicle recovery operations.
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Patterson, William Ray. „DEVELOPMENT OF A ROCKET MOTOR TEST SYSTEM AND A STUDY OF HYBRID ROCKET FUEL GRAINS“. MSSTATE, 2009. http://sun.library.msstate.edu/ETD-db/theses/available/etd-07062009-120546/.
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A rocket test system was developed and fabricated for the purpose of testing hybrid rocket motors. The test system includes a rocket test stand, load cell, and data acquisition system that is capable of safely and accurately recording thrust data from each burn. This paper documents the test system design and operation. The test system has been used to study the performance results from using multiple types of fuel utilized in hybrid motor systems. The types of hybrid motors used typically have thrust values below 1000 lbf. Along with different fuels, different motor configurations were also used during testing to determine if each hybrid rocket fuel reacted similarly under altering conditions.
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Rock, Brevin Shae. „Two-patch predator-prey system coupled with migration of both species“. View electronic thesis (PDF), 2009. http://dl.uncw.edu/etd/2009-3/Rockb/brevinrock.pdf.
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Holmeros, Linus. „Data acquisition system for rocket engine hot fire testing“. Thesis, KTH, Maskinkonstruktion (Inst.), 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-99495.
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ECAPS har utvecklat ett unikt drivmedel med tillhörande raketmotor för satellitstyrning som skall kunna ersätta Hydrazin, vilket idag är det vanligaste bränsle ombord på satelliter. Hydrazin är extremt giftigt och cancerogent. Det nya drivmedlet har 6 % högre specifik impuls samt 30 % högre densitetsimpuls jämfört med Hydrazin. Dessutom utgör ECAPS drivmedel en betydligt mindre risk för människa och miljö. Denna rapport innefattar en litteraturstudie om raketmotorer som används på satteliter samt hur testmiljön är uppbyggd av ECAPS där de utvecklar egna motorer. En motor beskrivs först generellt från bränsletank till dysutlopp och kompletteras med teoretiska härledningar av användbara begrepp. För vidareutveckling av nya raketmotorer har det befintliga motortestsystemet för få mätkanaler och begränsad samplingshastighet (2 kHz). Vidare är operatörsinterface och mjukvaran i behov av uppgradering samt att antalet kanaler behöver bli fler .Rapporten behandlar implementeringen av ett nytt mätsystem som är skrivet i Labview 8.6 vilket har gett en förbättring av t.ex. prestanda, stabilitet och gränssnitt. Samplingsfrekvensen är nu 10 kHz på 24 kanaler med marginal för utbyggnad upp till 40 kanaler, larmfunktioner finns på temperaturgivare och valfria analoga givare, gränssnittet är logiskt och mer ergonomiskt samt att spårbarheten för alla typer av körningar sparas i unika loggar.ECAPS has developed a unique propellant with a rocket engine which can be used to control satellites and replace Hydrazin which today is the most common fuel onboard on satellites. Hydrazin is extremely toxic and cancerogenic. The new propellant offers 6 % better specific impulse and 30 % better density impulse compared to hydrazine. ECPAS´s propellant also provides significant lower risks for both man and environment. The report includes a literature study about rocket engines which can be used on satellites and how the test environment is arranged where ECAPS develops their engines. The rocket engine is first generally described and then complemented a theoretical derivation of common concepts. For further development of new rocket engines the present engine test system has too few sensor channels and limited sampling capability (2 kHz). The operator interface and software can be upgraded and the number of channels needs to increase. This report treats the implementation of a new test system which is written in Labview 8.6 and has improved for example performance, stability and interface. The sampling frequency is now 10 kHz on 24 channels with a margin for up to 40 channels, alarm functions exists on both temperature and multiple choice sensors, the user interface is logic and more ergonomic together with increased traceability for different types of tests which are saved in unique logs.
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Chammam, Oussama. „Localization system and remote cutter for sounding rocket experiment“. Thesis, KTH, Skolan för elektro- och systemteknik (EES), 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-199275.
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Miquel, Valentin. „Propellant Feeding System of a Liquid Rocket With Multiple Engines“. Thesis, KTH, Rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-276460.
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Multiengine first stages are the new trend in recent rockets. Reusability and an oxygen/methane based engine complete this picture. ArianeGroup wants to develop its own rocket following these principles. This thesis presents the study of the feeding system for a seven Prometheus engine rocket. Several ways of connecting propellant tanks to engines were proposed and analyzed. Two configurations were selected and studied with more detail. One consists of a main feeding line which is then split in seven secondary lines. The other one adds one rank of pipes to reduce the number of feeding valves. Their performances were assessed according to classic space industry drivers. Furthermore, the impact of the two solutions on the efficiency of the tank was evaluated. CAD drawings and simulation models were made and could be a base for future work if one of the systems is chosen. The study shows that a falcon 9 like feeding system is performant in terms of mass and pressure losses but another cost-effective configuration is possible and gives good results.Första stegen med flera motorer är den nya trenden i de senaste raketerna. Återanvändbart och en syre och metan-baserad motor kompletterar denna bild. ArianeGroup vill utveckla sin egen raket enligt dessa principer. Denna avhandling presenterar studien av drivmedelsrör för en sju Prometheus-motorraket. Flera sätt att ansluta drivmedelstankar till motorer föreslogs och analyserades. Två konfigurationer valdes ut och studerades mer detaljerat. En består av en huvudlinje som sedan delas upp i sju sekundära linjer som på SpaceX Falcon 9. Den andra lösningen lägger till en rang av rör för att minska antalet ventiler. Deras prestanda utvärderades först enligt klassiska kriterier för rymdindustrin. Dessutom utvärderades de två lösningarnas påverkan på tankens effektivitet. CAD-ritningar och simuleringsmodeller gjordes och kan vara en bas för framtida arbeten om ett av systemen väljs. Studien visar att ett Falcon 9-liknande konfiguration har bättre prestanda när det gäller massa och tryckförluster men en annan kostnadseffektiv konfiguration är möjlig och ger goda resultat.
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MacLean, Steven M. „Modeling and Simulation of a Sounding Rocket Active Stabilization System“. DigitalCommons@CalPoly, 2017. https://digitalcommons.calpoly.edu/theses/1735.
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The Horizon Simulation Framework is a modeling and simulation framework developed to verify system level requirements. In this thesis, the framework is extended to include the Dynamic position type that existed in the early development phase of the framework. The Dynamic position type is tested through the modeling and simulation of a sounding rocket. An active control system based on linear-quadratic regulator (LQR) control theory is implemented and tested in the simulation to determine the overall effect on altitude. A first order aerodynamics and aeroprediction model are created within the framework to allow for rapid changes early in the design process of the sounding rocket. The flight dynamics are compared to two different sounding rocket flights and the aeroprediction model is validated against public wind tunnel test data.
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Kirkpatrick, Charles R., und A. Ayban Tuncay. „On The Move, Interactive Telemetry Data Acquisition System for the Multiple Launch Rocket System (MLRS)“. International Foundation for Telemetering, 1993. http://hdl.handle.net/10150/611851.
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International Telemetering Conference Proceedings / October 25-28, 1993 / Riviera Hotel and Convention Center, Las Vegas, NevadaThis paper describes the Launcher Instrumentation and Data Acquisition System (LIDAS) that has been developed for real-time monitoring and simultaneous recording of a diverse set of data buses on a moving MLRS launcher. The launcher onboard instrumentation consists of a central Bus Data Conversion Module (BDCM) and several specialized, intelligent "break-in" boxes. The break-in boxes collect and tag the data by using the IRIG-B standard time-code, and transfer them to the BDCM using a unique asynchronous scheme. The BDCM is built around an Intel 80960CA processor board in a VME bus environment. It coordinates all the data traffic and also stores selected data to an onboard Flash ROM data storage unit. The data from different MLRS buses are combined into a 1 megabits per second RS4-22 serial stream and telemetered to a ground station, where the user interface is provided through an IBM PC/AT type computer with touch-screen controls. The developed PC software offers several data monitoring options with engineering-unit conversions and allows simultaneous recording on a hard-disk. Because of its interactive capabilities, the system is also well suited for personnel training.
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Sellers, Jerry Jon. „Investigation into hybrid rockets and other cost-effective propulsion system options for small satellites“. Thesis, University of Surrey, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.309201.
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Protz, Christopher S. (Christopher Stephen) 1977. „Systems analysis of a microfabricated storable bipropellant rocket engine“. Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/9297.
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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2000.Includes bibliographical references (leaves 95-97).
This thesis discusses the systems analysis of a storable bipropellant micro-rocket engine. Micro-rockets are built using MEMS technology and are projected to deliver a thrust to weight ratio up to two orders of magnitude greater than conventional rocket motors at small thrust levels making them very attractive for satellite propulsion applications and propulsion of very small launch vehicles. Several propellant combinations and engine cycles have been analyzed. Propellant combinations have been evaluated for a 125 atm combustion chamber on the basis of their performance, handling, and cooling properties. A non-toxic hydrogen peroxide/ethanol combination (302 s Isp) is chosen over a nitrogen tetroxide/hydrazine combination (322 s Isp) and a hydrogen peroxode/JP-7 combination (315 s Isp) on the basis of handling and cooling properties. Studies indicate that nitrogen tetroxide/hydrazine expander and decomposition topping cycles and hydrogen peroxide/ethanol and hydrogen peroxide/JP-7 decomposition topping cycles are feasible. It is shown that a 300 atm turbopump feed system is possible while further investigations on bearings and pump design are required to fully validate the concept. The analysis suggests that the storable bipropellant micro-rocket engine concept is feasible and identifies the engineering challenges ahead.
by Christopher S. Protz.
S.M.
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Brodén, Daniel, und Patrick Magnusson. „Data acquisition and communication systems for sounding rocket experiment“. Thesis, KTH, Skolan för elektro- och systemteknik (EES), 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-199274.
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Romanov, Artyom. „Rocket Engine System Analysis : Vinci Engine Turbines Analysis, Volvo Aero Corp“. Thesis, Linköping University, Linköping University, Linköping University, Applied Thermodynamics and Fluid Mechanics, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17766.
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Major part of the current work describes the development of the update methodology for onedimensional code (TML) currently used at Volvo Aero Corporation during turbine design process. The methodology is then applied and tried out in a general engine analysis (GESTPAN).
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Dissel, Adam F. „Comparative system analysis of reusable rocket and air-breathing launch vehicles“. College Park, Md. : University of Maryland, 2005. http://hdl.handle.net/1903/2939.
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Thesis (M.S.) -- University of Maryland, College Park, 2005.Thesis research directed by: Dept. of Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.
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Harper, James M. „Pocket Rocket: A 1U+ Propulsion System Design To Enhance CubeSat Capabilities“. DigitalCommons@CalPoly, 2020. https://digitalcommons.calpoly.edu/theses/2218.
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The research presented provides an overview of a 1U+ form factor propulsion system design developed for the Cal Poly CubeSat Laboratory (CPCL). This design utilizes a Radiofrequency Electrothermal Thruster (RFET) called Pocket Rocket that can generate 9.30 m/s of delta-V with argon, and 20.2 ± 3 m/s of delta-V with xenon. Due to the demand for advanced mission capabilities in the CubeSat form factor, a need for micro-propulsion systems that can generate between 1 – 1500 m/s of delta-V are necessary.
By 2019, Pocket Rocket had been developed to a Technology Readiness Level (TRL) of 5 and ground tested in a 1U CubeSat form factor that incorporated propellant storage, pressure regulation, RF power and thruster control, as well as two Pocket Rocket thrusters under vacuum, and showcased a thrust of 2.4 mN at a required 10 Wdc of power with Argon propellant. The design focused on ground testing of the thruster and did not incorporate all necessary components for operation of the thruster. Therefore in 2020, a 1U+ Propulsion Module that incorporates Pocket Rocket, the RF amplification PCB, a propellant tank, propellant regulation and delivery, as well as a DC-RF conversion with a PIB, that are all attached to a 2U customer CubeSat for a 3U+ overall form factor. This design was created to increase the TRL level of Pocket Rocket from 5 to 8 by demonstrating drag compensation in a 400 km orbit with a delta-V of 20 ± 3 m/s in the flight configuration. The 1U+ Propulsion Module design included interface and requirements definition, assembly instructions, Concept of Operations (ConOps), as well as structural and thermal analysis of the system. The 1U+ design enhances the capabilities of Pocket Rocket in a 1U+ form factor propulsion system and increases future mission capabilities as well as propulsion system heritage for the CPCL.
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Farquharson, James. „Permeability evolution in volcanic systems : field, laboratory, and numerical investigations“. Thesis, Strasbourg, 2016. http://www.theses.fr/2016STRAH018/document.
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La perméabilité est une propriété essentielle notamment pour déterminer la nature explosive des volcans, ainsi que pour de nombreuses autres applications scientifiques et industrielles dans les environnements où l'écoulement du fluide est une préoccupation majeure. Combinant des méthodes expérimentales de déformation des roches en laboratoire, des approches de terrain, de la modélisation numérique, et des analyses systématiques de microstructure, ce travail a mis en évidence le caractère complexe de la formation et la destruction des réseaux poreux dans le magma et des roches volcaniques. La compétition entre les processus dilatants (qui augmentent la porosité) et compactants (qui la diminuent) exerce une influence sur les propriétés de transport des fluides à la fois dans le magma et dans la roche volcanique solidifiée. Ces processus incluent la vésiculation et la croissance des bulles dans le conduit, la rupture et la compression du magma, la fracturation issue du refroidissement et fracturation induite par le transport, ainsi que la déformation pendant ou après la mise en place des matériaux, et la densification par frittageThe permeability of various volcanic materials is an essential parameter governing the explosive behaviour of volcanic systems, as well as being important in many other scientific and industrial applications in environments where fluid flow is a major concern. Combining experimental rock deformation methods with field measurements, numerical modelling, and systematic analyses of rock microstructure, this work explores the complexities involved in the formation and destruction of porous networks in magma and volcanic rocks, addressing how permeability can evolve in volcanic systems. Competition between dilatant processes (which increase porosity) and compactant processes (which decrease porosity) influences the fluid transport properties both in the conduit-dwelling magma and in solidified edifice rock. These processes include (but are not limited to) vesiculation and bubble growth in the conduit, fracture and compaction of magma, post-emplacement thermal or mechanical fracturing, strain-induced deformation, and viscous sintering
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Biddy, Christopher Lorian. „Development of a High Performance Micropropulsion System for CubeSats“. DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/150.
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Picosatellites are defined as satellites with a mass between 0.1 and 1kg (Miniaturized satellite). Picosatellites are typically designed to work together or function in formations (Miniaturized satellite). A specific type of Picosatellite known as CubeSats were introduced in 1999 and since then have increased in popularity so that there are now over 80 CubeSat programs around the world. CubeSats are defined as cubic units 10cm on each side and no more than 1kg in mass. CubeSats are required to conform to the CubeSat Standard created by California Polytechnic State University and Stanford University and be compatible with Cal Poly’s P-POD deployment system (Toorian, 2005). Some CubeSat uses include earth imaging, communications projects and various scientific experiments. CubeSats currently require attitude control and in the future, may require, maintaining a specific orbit, or changing orbit. With this ability many new activities may be possible for CubeSats. These activities could include rendezvous, vehicle inspection, formation flying and de-orbiting. For these activities to be possible, a high performance propulsion system is required. The goal of this thesis is to design and test an affordable, safe, and effective micro-propulsion system for CubeSats.
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Haider, Fredrik. „Optical System for Impact Determination of Sounding Rockets“. Thesis, KTH, Rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-280157.
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To be able to ensure range safety and quickly recover the rocket and any on-board experiment, it is essential to be able to track the rocket. For sounding rocket launches at Esrange, this is typically done with radar or rocket telemetry, it has, however, recentlybecome of interest to do so with an optical system. This thesis develops the necessary methods for an optical system used to track and reconstruct the trajectory of a sounding rocket. It further discusses the limitations of such a system, given the hardware andinfrastructure available. Finally, some of the methods are tested with previous rocket footage showing that the suggested method works well for the available test cases. The full method uses foreground detection to detect the rocket in the image and using thisdata from multiple cameras combine to triangulate the 3D-coordinates of the rocket. A simple calibration method for the cameras is proposed, and future work to improve the capabilities of the system are proposed. The results show reliable tracking of the rocket,but raises concern in the viability of using current hardware for tracking the rocket during daytime due to difficulties in the visibility of the rocket in these conditions. The developed methods are foremost suggested to be used in nighttime conditions.För att kunna säkerställa säkerheten vid en raketuppskjutning och för att snabbt kunna återhämta raketen och alla experiment ombord är det viktigt att kunna spåra raketen. För sondraketuppskjutningar vid Esrange görs detta vanligtvis med radarellerrakettelemetri, men det har nyligen blivit av intresse att göra det med ett optiskt system. Detta examensarbete utvecklar de nödvändiga metoderna för ett optiskt system som används för att spåra och rekonstruera banan för sondraketer uppskjutna av SSC. Den diskuterar vidare begränsningarna för ett sådant system,givet den tillgängliga hårdvaran och infrastrukturen. Slutligen testas några av de metoder som utvecklats med tillgängliga testdata. Metoden som utvecklats använder förgrundsdetektering för att upptäcka raketen i bilden och använderdenna data från flera kameror för triangulering av raketens 3D-koordinater. En enkel kalibreringsmetod för kamerorna föreslås och framtida arbete för att förbättra systemets kapacitet föreslås. Resultaten visar pålitlig spårning av raket, men visaräven att nuvarande hårdvara troligtvis inte är tillräcklig för att spåra raket under dagtid. De utvecklade metoderna är huvudsakligen bäst ämnande för uppskjutningar på natten.
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Blumber, Eric Joseph. „Testing of a Magnetically Levitated Rocket Thrust Measurement System Demonstrator for NASA“. Thesis, Virginia Tech, 2002. http://hdl.handle.net/10919/33753.
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Existing thrust measurement systems (TMSs) at NASA Stennis Space Center use strain gauges and flux plates to measure forces produced by a test article. Alignment and calibration can take two weeks or more every time a piece of hardware or test article is changed. Cross axis loading is also problematic because it is impossible to perfectly align the flex plates and strain gauges in the thrust direction. In response to these problems, a magnetically levitated thrust measurement system has been proposed and a 300lb capacity demonstrator has been designed and built. In this design, the magnetic bearings work concurrently as support bearings and force measurement devices. The demonstrator consists of a floating frame that is completely levitated within a fixed frame by four support bearings carrying loads in the x- and y-direction and seven thrust bearings carrying loads in the z- or thrust direction. Joe Imlach of Imlach Consulting Engineering designed the demonstrator and magnetic bearing components, while Virginia Tech's role has been the application of the multipoint calibration technique including code development, the implementation of a 128-channel data acquisition system, and the overall test verification of the TMS demonstrator.A turnbuckle assembly and magnetostrictive actuator are used in series with a conventional load cell for static and dynamic testing, respectively. Both current based and flux based force equations were used to measure the reaction forces at the bearings. The static results using the current based equations including the current based fringing equations resulted in accuracies of 93% of full load, while the static results using the flux based equations including the flux based fringing equations resulted in accuracies of 99.5% of full load. These accuracies can be compared to accuracies of 83-90% seen in previous work using magnetic bearings to measure forces by monitoring currents and to accuracies of about 99% in previous work using magnetic bearings to measure forces by monitoring fluxes. All of the improved accuracies were made possible through the implementation of a calibration technique known as the multipoint method and the implementation of a gap dependent fringing correction factor developed by Joe Imlach. The demonstrator was not outfitted with accelerometers so the inertia of the floating frame could not be accounted for, limiting the scope of dynamic testing. However, the tests confirmed the ability of the demonstrator to measure dynamic loads in general.Master of Science
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Lundkvist, Emil, und Hont Markus Silberstein. „Construction and Implementation of Tracking System for the ISAAC Sounding Rocket Experiment“. Thesis, KTH, Fysik, 2013. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-129344.
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The ISAAC rocket experiment is part of the REXUS–15 payload. It has two free-falling units performing infrared spectroscopy between them. One of the free-falling units will actively track the other in the sky so as to enable continuous measurements. In this thesis report, the design of this tracking solution is described. The general concept of the tracking process is outlined, upon which the conceptuals as well as the hardware, software and firmware of each subsystem are explained. Tests of respective subsystems are conducted and conclusions are drawn pertaining to the accuracy and suitability of each subsystem for the tracking system. Index Terms —Tracking system, Sounding Rocket Experiment, VHDL, REXUS, I 2C, FPGA, CMOS Camera Sensor, Sun Sensing, Hardware Design, Software Design
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Ewig, Ralph. „Identification of a physically idealized human rated rocket based interplanetary transportation system /“. Thesis, Connect to this title online; UW restricted, 2006. http://hdl.handle.net/1773/9974.
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Vernacchia, Matthew T. „Development, modeling and testing of a slow-burning solid rocket propulsion system“. Thesis, Massachusetts Institute of Technology, 2017. http://hdl.handle.net/1721.1/112515.
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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.Cataloged from PDF version of thesis.
Includes bibliographical references (pages 163-168).
Small, unmanned aerial vehicles (UAVs) are expanding the capabilities of aircraft systems. However, a gap exists in the size and capability of aircraft: no aircraft smaller than 10 kilograms are capable of flight faster than 100 meters per second. A small, fast aircraft requires a propulsion system which is both miniature and high-power, requirements which current UAV propulsion technologies do not meet. To meet this need, a slow-burning solid rocket motor has been developed. Such motors require slow-burning solid propellants with tailorable burn rate. This thesis reports experimental results and combustion theory for a slow-burning solid propellant. It also describes a rocket motor designed to use this propellant, and the manufacturing process used to produce it. This propellant burns slowly enough for the low-thrust, long-endurance needs of UAV propulsion. Its burn rate can be predictably tailored by addition of the burn rate suppressant oxamide. Further, this thesis presents a concept for a small, fast aircraft designed around this novel propulsion technology. The motor integrates elegantly into the aircraft's structure, and compact thermal protection system insulates other vehicle systems from the heat of combustion. These results demonstrate the feasibility slow-burning rocket propulsion systems, and their application to small aircraft. It should be possible for small, rocket-propelled UAVs to sustain powered, transonic flight for several minutes. With this technology, kilogram-scale UAVs could be able to quickly deploy over tens of kilometers, and fly joint missions alongside manned fighter jets.
by Matthew T. Vernacchia.
S.M.
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Law, Boon-Chuan. „UNCERTAINTY ANALYSIS FOR ROCKET-BASED COMBINED CYCLE (RBCC) SYSTEMS TESTING“. MSSTATE, 2003. http://sun.library.msstate.edu/ETD-db/theses/available/etd-07152003-174339/.
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General uncertainty analysis was used to evaluate the performance of a Rocket-Based Combined Cycle (RBCC) engine system. To estimate the uncertainties of test results, uncertainties of basic measurements such as temperature, pressure, mass flow rate, and thrust were determined. The desired test results of interest included specific impulse and characteristic velocity. Various possible test facilities were reviewed to obtain background information and example test run conditions. Based on the test run conditions, five methods of determining specific impulse were evaluated. Also, theoretical and actual characteristic velocities were analyzed to evaluate C* efficiency. Initially, general uncertainty analyses were completed relative to 1% accuracy for each measured variable. Then, cases were run using more realistic uncertainty estimates. The relative contributions of the different variables? uncertainties to the overall uncertainty of the selected performance parameters were also calculated. This process helps to identify the critical measurements from an uncertainty standpoint and can be a significant guide in the cost effective use of resources to reduce the test uncertainty.
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Colonno, Michael Richard. „A multidiscip[l]inary optimization methodology for rocket vehicle systems /“. May be available electronically:, 2007. http://proquest.umi.com/login?COPT=REJTPTU1MTUmSU5UPTAmVkVSPTI=&clientId=12498.
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Siebert, Joseph R. „Design hazard analysis, and system level testing of a university propulsion system for spacecraft application“. Diss., Rolla, Mo. : Missouri University of Science and Technology, 2009. http://scholarsmine.mst.edu/thesis/pdf/Siebert_09007dcc8063c59e.pdf.
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Thesis (M.S.)--Missouri University of Science and Technology, 2009.Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed April 14, 2009) Includes bibliographical references (p. 201-203).
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Rocker, Andrea [Verfasser], und Ilme [Akademischer Betreuer] Schlichting. „Epsilon/Zeta Toxin-Antitoxin Systems in Gram-negative Bacteria / Andrea Rocker ; Betreuer: Ilme Schlichting“. Heidelberg : Universitätsbibliothek Heidelberg, 2016. http://d-nb.info/1180614038/34.
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Hafström, Johan H., und Malin Nordström. „Systemförvaltning : faktisk verksamhet, problem och möjligheter“. Thesis, Institutionen för Informationsteknologi och Systemvetenskap, Högkolan i Östersund, 1991. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-142874.
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Syftet med föreliggande arbete är att undersöka hur företag och organisationer förvaltar sina informationssystem, om Applicerad Modell (Hafström, Nordström; 1991) innehåller de delar som krävs för en fungerande systemförvaltning samt att med ledning av erhållen information diskutera kring problem och möjligheter med systemförvaltning. Vi genomförde en litteraturstudie och intervjuade personer som är inblandade I systemförvaltningsprocessen. Resultatet av litteraturstudien presenteras genom definitioner av begrepp och resultatet av tre vägledande undersökningar. Därefter presenteras en sammanfattning av de intervjuer vi genomfört. Utifrån erhållen information utvecklar vi definitionen av systemförvaltningsbegreppet. Applicerad Modell utvecklas och resultatet blir en ny modell kallad Raket Förvaltningsmodell. Vidare diskuterar vi kring problem och möjligheter med systemförvaltning och slutligen ges synpunkter på hur man skall starta arbetet med att strukturera systemförvaltningsprocessen.The aim with the present work is to examine how corporations and organizations maintain their information systems, if the Applied Mode! (Hafström, Nordström; 1991) contain all parts required for working system maintenance and according to this discuss problems and possibilities of system maintenance. We realized a literature study and interviewed people who are involved in the process of system maintenance. The result of the literature study is presented by definitions of conceptions and the result of three examinations. A summary of the interviews is made. From the received information we developed the definition of the system maintenance conception. Applied Mode! is developed and the result is Rocket Maintenance Model. Further on we discuss problems and possibilities of system maintenance and finally we are giving our opinion how to start the work by structuring the system maintenance process.
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Serediuk, Vadym. „Návrh průkazných statických pevnostních zkoušek letounu v kategorii UL“. Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2021. http://www.nusl.cz/ntk/nusl-443247.
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The diploma thesis involves the design of certification static strength tests for the newly developed aircraft of the TL-Ultralight company. At the beginning of the work, the theory of aircraft testing is generally discussed with emphasis on static strength tests. Furthermore, an analysis of the requirements of the Czech regulation UL 2 and the German LTF-UL, which represent the certification basis for this aircraft, is performed. The requirements of regulations on the construction of the aircraft (or its individual parts) and the requirements for strength tests are discussed in detail. Based on the regulation and the provided calculation protocols, individual test cases and test plans of the wing, tail surfaces, engine bed, and chassis are calculated and prepared. In the end, the calculation of the rocker system and the basic design of jigs are performed.
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Burchill, Johnathan Kerr. „Development of a real-time video camera system for the HiRES sounding rocket“. Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1997. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp01/MQ29974.pdf.
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Bairstow, Brian Kenichi. „Effectiveness of integration of system-level optimization in concurrent engineering for rocket design“. Thesis, Massachusetts Institute of Technology, 2006. http://hdl.handle.net/1721.1/35582.
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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2006.Includes bibliographical references (p. 110-111).
Integrated concurrent engineering is a method for rapid conceptual design. Previous study has suggested that integration of system-level optimization techniques into integrated concurrent engineering can benefit the design process. In order to confirm and strengthen these results further study was carried out. A two-stage liquid rocket software model was created to serve as a complex multi-disciplinary design problem. Several design session trials were run with the goal of optimizing the rocket in performance and cost. Some design teams used optimization along with integrated concurrent engineering, while others only used integrated concurrent engineering. The results from the two design methods were compared in several metrics, and including optimization alongside concurrent engineering shows a marked benefit in some areas.
by Brian Kenichi Bairstow.
S.M.
34
MABBOUX, ROMAIN. „Optimization of the pressurization system of the Themis reusable rocket first stage demonstrator“. Thesis, KTH, Skolan för industriell teknik och management (ITM), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-301295.
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The design of complex systems such as a launcher, or subsystems like its pressurization system, is known to be fastidious and expensive especially in the space domain. However, the recent emergence of new actors in this domain has been a game changer, binding these systems to fulfil more and more requirements (cheap, efficient, rapidly produced, aesthetic, environmentally friendly…) in order to compete with the market. For these reasons, engineers now need more than ever to consider the full picture of a system or subsystem in order to optimize it. In this context, this document aims to present the method and the results obtained in the optimization of the pressurization system of a reusable rocket first stage named Themis 3. The modelling of the pressurization system has been realized through a software called Geeglee. In order to cover as many impacts of this system as possible, an important part of the rocket stage has been considered and modelled (from the pressurization gases to the propellant tanks, passing by the pressurant and propellant feeding lines). Three High Level Requirements (HLR) have been identified as of major importance for the trade-off in the design of the pressurization system: the total mass impact, the total Recursive Cost (RC) impact and the total Non-Recursive Cost (NRC) impact. This optimization has in particular permitted to confirm some well-known results, so to say that exogenous pressurization systems represent a smaller mass impact on the vehicle, at the expense of a higher RC compared with autogenous systems.Utformningen av komplexa system, som till exempel en bärraket, eller delsystem som dess trycksättningssystem, är känd för att vara krävande och kostsam, särskilt inom rymdteknikområdet. Den senaste tidens uppkomst av nya aktörer på detta område har dock förändrat spelregler då dessa system tvingas uppfylla allt fler krav (billiga, effektiva, snabbt producerade, estetiska, miljövänliga etc.) kunna vara konkurrenskraftiga på marknaden. Av dessa skäl måste ingenjörer nu mer än någonsin beakta hela bilden av ett system eller delsystem för att kunna optimera det. I detta sammanhang syftar detta dokument till att presentera metoden och resultaten från optimeringen av trycksättningssystemet för en återanvändbar rakets första steg som heter Themis 3. Modelleringen av trycksättningssystemet har genomförts med hjälp av ett systemmodelleringsverktyg som kallas Geeglee. För att täcka in så många effekter av detta system som möjligt har en viktig del av raketsteget beaktats och modellerats (från trycksättningsgaserna till drivmedelstankarna, via tryck- och drivmedelsmatningsledningarna). Tre krav på hög nivå har identifierats som mycket viktiga för avvägningen vid utformningen av trycksättningssystem konstruktion: den totala masspåverkan, den totala icke-rekursiva kostnaden och den totala rekursiva kostnaden. Denna optimering har framför allt gjort det möjligt att bekräfta vissa välkända resultat, dvs. att exogena trycksättningssystem ger en mindre masspåverkan på fordonet, på bekostnad av en högre RC jämfört med autogena system.
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Myers, Neil B. „Analysis of a Rocket-Borne Resonant Scatter System for Measurement of Atomic Oxygen“. DigitalCommons@USU, 1985. https://digitalcommons.usu.edu/etd/4848.
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A computer model has been developed at Utah State University for interpreting the results of a rocket-borne resonant scatter measurement system using 1304 A radiation. Atomic oxygen densities are obtained from 65 to 140 km from three rocket flights. The resolution of the system is < 0.1 km, and considerable structure has been observed. The variety of shapes exhibited by the three profiles suggest a dynamic nature to atomic oxygen density profiles in the lower ionosphere. Maximum densities between 2.6 x toll and 1.2 x 1012 cm-3 were observed at altitudes between 92 and 95 km.
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Fidjeland, Leo. „Construction and analysis of a GPS and localization system for sounding rocket experiment“. Thesis, KTH, Skolan för elektro- och systemteknik (EES), 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-199317.
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Ueda, Yoshikatsu. „Study on High Performance System of Plasma Wave Receiver for Satellite/Rocket Observations“. 京都大学 (Kyoto University), 2004. http://hdl.handle.net/2433/147593.
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Wu, Jenq-dah. „Time-dependent, mixed-mode fracture of solid rocket motor bondline systems /“. Digital version accessible at:, 1999. http://wwwlib.umi.com/cr/utexas/main.
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Witter, Jonathan Keay. „Modeling for the simulation and control of nuclear reactor rocket systems“. Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/12755.
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Seubert, Carl Reiner. „Refrigerant-based propulsion system for small spacecraft“. Diss., Rolla, Mo. : University of Missouri-Rolla, 2007. http://scholarsmine.umr.edu/thesis/pdf/Carl_Reiner_Seubert_Masters_Thesis_09007dcc8031c34d.pdf.
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Thesis (M.S.)--University of Missouri--Rolla, 2007.Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed May 11, 2007) Includes bibliographical references (p. 115-119).
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Watson, C. A. „Roche tomography of cataclysmic variables“. Thesis, University of Sheffield, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.269267.
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Doan, Andrew W. „3-D flow and performance of a rocket pump inducer at design and off-design flow rates“. Thesis, This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-11242009-020251/.
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Rozenbeek, David, und Keyserlingk Erik von. „Recovery and Flight Data Recording System for Free Falling Units Ejected From Sounding Rocket“. Thesis, KTH, Skolan för elektro- och systemteknik (EES), 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-214743.
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The aurora phenomena is a remarkable sight, commonlyrefereed to as polar or northern lights. A previous spaceexperiment SPIDER was dedicated to measure electric fieldsand characterize plasma properties in the aurora, using tenFree Falling Units (FFU) ejected from a sounding rocket. Theexperiment was successful but some problems arose. A newexperiment WOLF is committed to solve those problems andre-doing the experiment.This paper describes the process of developing a new recoveryand flight data recording system for the WOLF experiment, usingheritage from the previous SPIDER experiment. The developedsystem will be used on the upcoming WOLF experiment rocketlaunch in February 2018.The thesis analyzed hardware problems in previous design toimprove robustness and reliability, identified obsolete componentsfor replacement and added functionality for the new system. Anew hardware system was developed with schematics and PCBlayout ready for manufacturing. Also, plans for the firmware wasestablished. In the paper it is discussed about topics that shouldbe considered in the future work in developing the system andhow the system can be re-purposed for similar experiment in thefuture.
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Cox, Corry. „IMPLEMENTING A TACTICAL TELEMETRY STYSTEM FOR MULTIPLE LAUNCH ROCKET SYSTEM (MLRS) STOCKPILE RELIABILITY TESTING“. International Foundation for Telemetering, 2004. http://hdl.handle.net/10150/604935.
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International Telemetering Conference Proceedings / October 18-21, 2004 / Town & Country Resort, San Diego, CaliforniaThe Precision Fires Rocket and Missile Systems (PFRMS) Program Office continually undertakes Stockpile Reliability Testing (SRP) to ensure the validity of the accumulated weapons and increase the she lf life of these weapon systems. MLRS is a legacy weapon system that has been undergoing SRP testing for over 20 years. The PFRMS Program Office has a need for a miniature Tactical Telemetry System that will monitor the fuze performance of the MLRS Rocket during SRP testing. This paper will address a technical approach of how a small Tactical Telemetry System could be built to meet this requirement. The Tactical Telemetry system proposed in this paper will monitor fuze functions, operate across the wide environmental spectrum of the SRP tests, and physically fit in the nose area without altering the overall tactical rocket appearance or operation.
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Lokken, Patrick Bucknam. „Command and data handling systems for a multi-instrument sounding rocket payload“. Thesis, Montana State University, 2011. http://etd.lib.montana.edu/etd/2011/lokken/LokkenP0511.pdf.
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To improve our physical understanding of the solar transition region, the Multi-Order Solar EUV Spectrograph (MOSES) has been developed at Montana State University to perform imaging spectroscopy of the sun at extreme ultraviolet wavelengths. Launched first in 2006, the instrument performed simultaneous imaging and spectroscopy over a narrow band centered around 30.4 nm. The amount of science that can be accomplished with the instrument is limited by its optical bandwidth, which must be small to reduce ambiguity in its data. This limitation can be overcome by launching an array of instruments operating at different wavelengths, piecing together a comprehensive view of transition region activity on a wide bandwidth. However, the command and data handling (C&DH) system on the current MOSES payload cannot support multiple instruments, and a new system must be built to support the addition of more instrumentation. To this end, designs based on a centralized computer topology and a distributed computer topology have been created for a new C&DH system to support the existing MOSES instrument, an EUV Snapshot Imaging Spectrograph (ESIS) and an improved guide scope. It was found that the frame rate of the entire electro-optical system was limited mostly by the low sensitivity of the optics, and that the choice between the two is driven by the mass of the system and the amount of engineering effort required to build the system. The centralized system was found to be both lighter and easier to build, and therefore a centralized system is recommended for the second revision of the MOSES payload.
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Paquin, Jeremy(Jeremy David). „A systems-based analysis method for safety design in rocket testing controllers“. Thesis, Massachusetts Institute of Technology, 2019. https://hdl.handle.net/1721.1/122415.
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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, in conjunction with the Leaders for Global Operations Program at MIT, 2019Thesis: M.B.A., Massachusetts Institute of Technology, Sloan School of Management, in conjunction with the Leaders for Global Operations Program at MIT, 2019
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 122-123).
Boeing is the prime contractor for building the National Aeronautics and Space Administration (NASA) Space Launch System (SLS) core stage for upcoming exploration missions beyond low earth orbit. Due to the rigorous demands of safety on crew-rated spacecraft, the entire vehicle undergoes captive hot-fire testing before being delivered to NASA for actual flight operations. The hot-fire test is controlled by a suite of computers used to control the rocket segment and critical infrastructure interactions during the test. The complexity of the software and hardware used to control the test makes it difficult for traditional safety approaches to identify potentially unsafe system interactions by focusing only on component failures rather than overall system interactions. Traditional chain-of-failure safety analyses and reviews take significant resources and time to conduct while leaving possible gaps. This thesis discusses a method for analyzing safety of rocket test controllers by characterizing key indicators and developing a systems-based approach for hazard analysis using Systems-Theoretic Process Analysis (STPA). A resulting case study is applied for examination of a portion of the rocket testing controller system for comparison to traditional chain-of-failure events analyses. Appling STPA in the case-study resulted in 83% of the total work time needed to complete a comparable "ascent phase" analysis using FMEA. The STPA results are the same or meet a similar intent to those resolved in the FMEA with not gaps between the two methods. The recommended mitigation and constraints resulting from STPA are arguably more intuitive than those of the FMEA.
by Jeremy Paquin.
S.M.
M.B.A.
S.M. Massachusetts Institute of Technology, Department of Aeronautics and Astronautics
M.B.A. Massachusetts Institute of Technology, Sloan School of Management
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Bennett, Steven Russell. „Control and Stability of Upper Stage Launch Vehicle With Hybrid Arc-Ignition Attitude Control System“. DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7518.
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The Utah State University Propulsion Research Laboratory (USUPRL) has recently made significant developments in the area of hybrid rocket systems. This type of propulsion system incorporates a solid fuel and a gas or liquid oxidizer. Hybrid rocket systems are known for their inherent safety, reliability, and restart capability. Over the last several years, the USUPRL has successfully built and tested a hybrid rocket system comprising acrylonitrile butadiene styrene (ABS) plastic and gaseous oxygen (GOX). The system was demonstrated to be fully functional during ground, vacuum, and sub-orbital flight testing. Continuing forward, the USUPRL endeavors to extend the capabilities of this hybrid rocket system to in-space propulsion applications, such as an attitude control systems (ACS). This thesis investigates the feasibility of using the USU Green Hybrid Rocket as an ACS for an intermediate-sized launch vehicle. A computer simulation was developed to demonstrate the control and stability of the spacecraft under the influence of the ACS.
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Bartholomew, David L. „Spectral modeling of the SSME enhancements and a software system“. Ohio : Ohio University, 1992. http://www.ohiolink.edu/etd/view.cgi?ohiou1172083672.
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Langrová, Hana. „Vývoj českého penzijního systému po roce 1989 a možnosti jeho dalšího směřování“. Master's thesis, Vysoká škola ekonomická v Praze, 2015. http://www.nusl.cz/ntk/nusl-205883.
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The purpose of this thesis is an analysis of the development of the pension system in the Czech Republic since 1989. The emphasis is placed on reform provisions and on their impact on public budgets. Future direction is discussed next. The demographic development raises concerns about the financial sustainability of pension systems. The changes in the structure of the system were made after several years of discussions and a number of parametric adjustments. The question of sustainability is not closed yet. Recent changes are canceled and the system returned to the previous state. The reason was a lack of political and general agreement about this type of reform. The theoretical part deals with the definition of public budgets with a focus on social security. The importance and the function of pension systems are characterized in the next section. Pension systems are classified by the operator, by the method of calculating pension benefits and by the type of funding. Each pension system is based on tradition and is influenced by the development of society in the political, economic and social fields. In the practical part is performed the analysis of the pension system structured according to the periods. The impact of the reform provisions is illustrated on the state of public budgets. The thesis concludes that the initial efforts to change the system fundamentally will be replaced by attempts to implement minor adjustments. In the case of structural reform in the future it could be considered the application of modern pension theory, which recommends Pan-European pension system.
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Jung, Jackson H. (Jackson Hoa-Wai). „Modeling, and classical and advanced control of a solid rocket motor thrust vector control system“. Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/12473.
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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science, 1993.Includes bibliographical references (leaves 119-124).
by Jackson H. Jung.
M.S.