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Dissertations / Theses on the topic 'Satellite system'
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Anderson, Jason Lionel. "Autonomous Satellite Operations For CubeSat Satellites." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/256.
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In the world of educational satellites, student teams manually conduct operations daily, sending commands and collecting downlinked data. Educational satellites typically travel in a Low Earth Orbit allowing line of sight communication for approximately thirty minutes each day. This is manageable for student teams as the required manpower is minimal. The international Global Educational Network for Satellite Operations (GENSO), however, promises satellite contact upwards of sixteen hours per day by connecting earth stations all over the world through the Internet. This dramatic increase in satellite communication time is unreasonable for student teams to conduct manual operations and alternatives must be explored. This thesis first introduces a framework for developing different Artificial Intelligences to conduct autonomous satellite operations for CubeSat satellites. Three different implementations are then compared using Cal Poly's CP6 CubeSat and the University of Tokyo's XI-IV CubeSat to determine which method is most effective.
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Brengesjö, Carl, and Martine Selin. "Tracking System : Suaineadh satellite experiment." Thesis, KTH, Skolan för informations- och kommunikationsteknik (ICT), 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-52906.
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The purpose of this bachelor thesis is to present a tracking system for the Suaineadh satellite experiment. The experiment is a part of the REXUS (Rocket EXperiments for University Students) program and the objective is to deploy a foldable web in space. The assignment of this thesis is to develop a tracking system to find the parts from the Suaineadh experiment that will land on Earth. It is important to find the parts and recover all the data that the experiment performed during the travel in space. The implementation of this thesis investigates two different ways to track and find the experiment. The first way is to locate the experiment module by a Global Positioning System (GPS) and send the coordinates to a satellite modem, controlled by a programmed microprocessor. The other way is by using a radio beacon that sends a speciffic radio frequency. The results of this thesis presents a prototype for the tracking system with a GPS and the satellite modem and code example for the microprocessor. It also presents a working radio freqency beacon system on a Printed Circuit Board. The thesis had some unexpected incidents and had to change some directives. This rendered the work to take longer time then estimated. Despite the difficulties resulted this thesis in a working system to track the experiment.
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Smith, William Whitfield Jr. "A satellite interference location system." Diss., Georgia Institute of Technology, 1990. http://hdl.handle.net/1853/16879.
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Oiesen, Eric A. "A satellite signal recognition system." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-09052009-040513/.
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Gabor, Michael Joseph. "GPS carrier phase ambiguity resolution using satellite-satellite single differences /." Digital version accessible at:, 1999. http://wwwlib.umi.com/cr/utexas/main.
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Grungxu, Lungile Leonard. "Aspect of a hardware-in-the-loop integrated test system." Thesis, Stellenbosch : Stellenbosch University, 2003. http://hdl.handle.net/10019.1/53292.
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Thesis (MScEng)--University of Stellenbosch, 2003.ENGLISH ABSTRACT: A multiprocessor hardware-in-the-Ioop operating system was developed for the Integrated Test System (ITS) and is aimed at implementing the ITS as a space emulation vehicle. The thesis contains a study of satellite orbits, Kepler elements, geomagnetic fields and communication protocol between the processors. The system structure consists of an orbit generator, a core-operating system and is presented with a study of the satellite sensors. In implementing the orbit propagator, there was a need to pay special attention to the Halving algorithm, the Newton Raphson method and the True Solution. These algorithms were used to calculate the true anomaly angle as a function of eccentric anomaly. The communications protocol was tested and all the errors, with their solutions, have been discussed. A concept of a geomagnetic field emulator has also been included in the hardware-in-theloop operating system. The evaluation of those aspects of the system and the conclusion are presented together with recommendations.
AFRIKAANSE OPSOMMING: 'n multiprosesseerder Hardeware in die lus bedryfstelsel is ontwikkel vir 'n Geintegreerde Toets Stelsel (ITS) en poog om die ITS te implementeer as 'n ruimte emulasie stelsel. Die tesis behels die studie van sateliet wentelbane, Kepler wentelbaan elemente, geomagnetiese velde en kommunikasie protokolle tussen die prosesseerders. Die stelsel struktuur betaal uit 'n wentelbaan propageerder, 'n kern bedryfstelsel en 'n studie van satelliet instrumentasie. As 'n deel van die implementering van die wentelbaan propageerder is die halveer algoritme, Newton-Raphson algoritme en die ware oplossing as numeriese oplossings ondersoek. Die kommunikasie protokol is getoets en foute ondersoek en word bespreek. 'n konsep vir 'n Geomagnetiese veld emulasie word die hardeware in die lus stelsel ingesluit. Die stelsel word ge-ewalueer en die gevolgtrekkings en aanbevelings gemaak.
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Selva, Valero Daniel. "Rule-based system architecting of Earth observation satellite systems." Thesis, Massachusetts Institute of Technology, 2012. http://hdl.handle.net/1721.1/76089.
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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2012.Cataloged from PDF version of thesis.
Includes bibliographical references (p. 399-412).
System architecting is concerned with exploring the tradespace of early, high-level, system design decisions with a holistic, value-centric view. In the last few years, several tools and methods have been developed to support the system architecting process, focusing on the representation of an architecture as a set of interrelated decisions. These tools are best suited for applications that focus on breadth - i.e., enumerating a large and representative part of the architectural tradespace -as opposed to depth - modeling fidelity. However, some problems in system architecting require good modeling depth in order to provide useful results. In some cases, a very large body of expert knowledge is required. Current tools are not designed to handle such large bodies of knowledge because they lack scalability and traceability. As the size of the knowledge base increases, it becomes harder: a) to modify existing knowledge or add new knowledge; b) to trace the results of the tool to the model assumptions or knowledge base. This thesis proposes a holistic framework for architecture tradespace exploration of large complex systems that require a large body of expert knowledge. It physically separates the different bodies of knowledge required to solve a system architecting problem (i.e., knowledge about the domain, knowledge about the class of optimization or search problem, knowledge about the particular instance of problem) by using a rule-based expert system. It provides a generic population-based heuristic algorithm for search, which can be augmented with rules that encode knowledge about the domain, or about the optimization problem or class of problems. It identifies five major classes of system architecting problems from the perspective of optimization and search, and provides rules to enumerate architectures and search through the architectural tradespace of each class. A methodology is also defined to assess the value of an architecture using a rule-based approach. This methodology is based on a decomposition of stakeholder needs into requirements and a systematic comparison between system requirements and system capabilities using the rules engine. The framework is applied to the domain of Earth observing satellite systems (EOSS). Three EOSS are studied in depth: the NASA Earth Observing System, the NRC Earth Science Decadal Survey, and the Iridium GEOscan program. The ability of the framework to produce useful results is shown, and specific insights and recommendations are drawn.
by Daniel Selva Valero.
Ph.D.
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Asiri, Hassan M. "Steady motions of a satellite system." Thesis, University of Manchester, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.489508.
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This thesis considers two systems: a dumb-bell satellite which is a system of two point masses connected by a massless rigid rod, and a gyrostat consisting of a dumbbell satellite with a gyroscope attached. Stability of relative equilibria of the dumbbell satellite in two dimensions is studied, where two types of relative equilibrium are obtained, which correspond to two orientations: radial and tangential. The only relative equilibrium which is found to be stable is the radial position, and this stability is only satisfied when the length of the dumb-bell satellite is smaller than the radius of the orbit. The reduced energy-momentum method is used through the augmented Hamiltonian.
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Dunn, Nicholas Connor. "Satellite System Safety Analysis Using STPA." Thesis, Massachusetts Institute of Technology, 2013. http://hdl.handle.net/1721.1/85777.
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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013.CD-ROM contains 2 Excel spreadsheets.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 139-140).
Traditional hazard analysis techniques based on failure models of accident causality, such as the probabilistic risk assessment (PRA) method currently used at NASA, are inadequate for analyzing safety at the system level. System-Theoretic Accident Model and Processes (STAMP) shifts the focus of safety from preventing failures to that of a dynamic feedback control system that enforces behavioral constraints. System-Theoretic Process Analysis (STPA), the hazard analysis method based on STAMP, was applied to the launch and mission phases of a NASA/JAXA Global Precipitation Measurement (GPM) Core Observatory-based satellite. Exploiting the fact that nearly all satellites follow similar lifecycles and employ common functional architectures with relatively-decoupled, unique mission payloads, a template for future satellite STPA safety analyses was developed. The template seeks to aid and guide new STPA applications while reducing analysis time by providing the STPA analysis for many common satellite functions. Increasing pressure to reduce satellite mission costs has renewed interest in modular payloads. Traditional hazard analysis methods are dependent on the hardware used, so they must be redone for the entire system if the payload is changed. This repetition of work is time intensive and costly. STPA is the only hazard analysis method that may be performed early in development and without details of the system hardware implementation. Using the GPM-based satellite STPA analysis, the influence of the mission payload on safety at the system-level is considered. Five types of control action mismatch resulting from changing payloads were identified along with the corresponding additional STPA analysis required to ensure safety at the system level.
by Nicholas Connor Dunn.
S.M.
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Hammond, C., D. Beauvarlet, A. Kipple, R. Condit, T. Firestone, V. Ling, G. Morris, and D. Powers. "TELEMETERING SYSTEM FOR THE UA SATELLITE." International Foundation for Telemetering, 2000. http://hdl.handle.net/10150/607700.
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International Telemetering Conference Proceedings / October 23-26, 2000 / Town & Country Hotel and Conference Center, San Diego, CaliforniaThis student paper was produced as part of the team design competition in the University of Arizona course ECE 485, Radiowaves and Telemetry. It presents a telemetering system proposed for UASat, a small satellite being designed for launch in the year 2004. The overall system architecture is described, including the transducers used by each subsystem, the command and telemetry packet formats, the antennas and modulation schemes, the link budget, and some hardware recommendations. A discussion of the data analysis is also included.
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Brown, Barbie, Parminder Ghuman, Johnny Medina, and Randy Wilke. "A DESKTOP SATELLITE DATA PROCESSING SYSTEM." International Foundation for Telemetering, 1997. http://hdl.handle.net/10150/607552.
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International Telemetering Conference Proceedings / October 27-30, 1997 / Riviera Hotel and Convention Center, Las Vegas, NevadaThe international space community, including National Aeronautics and Space Administration (NASA), European Space Agency (ESA), Japanese National Space Agency (NASDA) and others, are committed to using the Consultative Committee for Space Data Systems (CCSDS) recommendations for low earth orbiting satellites. With the advent of the CCSDS standards and the availability of direct broadcast data from a number of current and future spacecraft, a large number of users could have access to earth science data. However, to allow for the largest possible user base, the cost of processing this data must be as low as possible. By utilizing Very Large Scale Integration (VLSI) Application-Specific Integrated Circuits (ASIC), pipelined data processing, and advanced software development technology and tools, highly integrated CCSDS data processing can be attained in a single desktop system. This paper describes a prototype desktop system based on the Peripheral Component Interconnect (PCI) bus that performs CCSDS standard frame synchronization, bit transition density decoding, Cyclical Redundancy Check (CRC) error checking, Reed-Solomon decoding, data unit sorting, packet extraction, annotation and other CCSDS service processing. Also discussed is software technology used to increase the flexibility and usability of the desktop system. The reproduction cost for the system described is less than 1/8th the current cost of commercially available CCSDS data processing systems.
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Pazzani, Michael, and Anne Brindle. "An Expert System for Satellite Control." International Foundation for Telemetering, 1985. http://hdl.handle.net/10150/615592.
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International Telemetering Conference Proceedings / October 28-31, 1985 / Riviera Hotel, Las Vegas, NevadaAs on-board satellite systems develop increased sophistication and autonomous capabilities, failures become fewer, but the diagnosis of the remaining failures becomes more complex. In addition, autonomy requirements for space vehicles are being issued along with requirements for reduced staffing of ground stations. Thus successful groundbased fault handling in the future will require greatly increased automation of fault detection and diagnosis. This paper investigates the use of an expert system as a ground system component for diagnosis. The diagnostic cycle of the system is presented, along with requirements for its knowledge base. The results of implementing the design to diagnose part of a satellite attitude control system are given. Knowledge acquisition for this problem centered on the generation and analysis of terminal displays of telemetry which look much like strip charts. Correct diagnosis by the expert system derived from the use of extensive telemetry analysis, operations and satellite status databases, and satellite modeling.
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Chintalapati, Lakshmi Venkata Bharadwaj. "Integration of Mission Control System, On-board Computer Core and spacecraft Simulator for a Satellite Test Bench." Master's thesis, Universitätsbibliothek Chemnitz, 2016. http://nbn-resolving.de/urn:nbn:de:bsz:ch1-qucosa-212663.
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The satellite avionics platform has been developed in cooperation with Airbus and is called „Future Low-cost Platform“ (FLP). It is based on an Onboard Computer (OBC) with redundant processor boards based on SPARC V8 microchips of type Cobham Aeroflex UT699. At the University of Stuttgart a test bench with a real hardware OBC and a fully simulated satellite is available for testing real flight scenarios with the Onboard Software (OBSW) running on representative hardware. The test bench as later the real flying satellite "Flying Laptop" – is commanded from a real Ground Control Centre (GCC). The main challenges in the FLP project were
- Onboard computer design,
- Software design and
- Interfaces between platform and payloads
In the course of industrialization of this FLP platform technology for later use in satellite constellations, Airbus has started to set up an in-house test bench where all the technologies shall be developed. The initial plan is to get first core elements of the FLP OBSW ported to the new dual-core processor and the new Space Wire(SpW) routing network. The plan also has an inclusion of new Mission Control Software with which one can command the OBC. The new OBC has a dual core processor Cobham Gaisler GR712 and hence, all the payload and related functionality are to be implemented only in a second core which involves a lot of low-level task distribution. The consequent SpW router network application and dual-core platform/payload OBSW sharing are entirely new in the field of satellite engineering.
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Clemons, Thomas M. "System analysis of a tactical multi-satellite communication system." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/26289.
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Tetewsky, Avram Ross Jeff Soltz Arnold Vaughn Norman Anszperger Jan O'Brien Chris Graham Dave Craig Doug Lozow Jeff. "Making sense of inter-signal corrections : accounting for GPS satellite calibration parameters in legacy and modernized ionosphere correction algorithms /." [Eugene, Ore. : Gibbons Media & Research], 2009. http://www.insidegnss.com/auto/julyaug09-tetewsky-final.pdf.
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"Author biographies are available in the expanded on-line version of this article [http://www.insidegnss.com/auto/julyaug09-tetewsky-final.pdf]""July/August 2009." Web site title: Making Sense of GPS Inter-Signal Corrections : Satellite Calibration Parameters in Legacy and Modernized Ionosphere Correction Algorithms.
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Davis, Mark J. (Mark Jeffrey). "Synchronization of system-of-systems interfaces in military satellite communications." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/43123.
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Thesis (S.M.)--Massachusetts Institute of Technology, System Design and Management Program, 2008.Includes bibliographical references (p. 207-212).
Military systems continue to become more complex and nearly all are now part of one or more system of systems (SoS). Military satellite communications programs have expanded over the last decade from three distinct satellite constellations with dedicated ground, ship, and airborne terminals to several existing and planned satellite constellations and dozens of multi-purpose terminal variants. Each of the new systems must operate with both legacy and new systems. This has given rise to many new external system interfaces that span the boundaries of large SoSs. Unsynchronized interface design and development has caused large amounts of scrap and rework in the design and development of the new military systems leading to adverse impacts including large cost growth and schedule delays. The Air Force Military Satellite Communications Systems Wing (MCSW) in Los Angeles, CA has begun to put a framework in place to manage SoS interfaces, but there are still big challenges ahead and room for improvement. This research collects data to quantify the performance of the present MCSW change management process. A value stream mapping and analysis effort along with a discrete even simulation model is conducted to identify areas for improvement in the as-is change management process and suggest an improved future-state change management process. The future-state change management process draws on best practices from the lean and SoS engineering literature to improve interface synchronization and significantly reduce process cycle time. This leaner and more effective future-state change management process could be applicable to many government acquisition program offices to save cost and schedule on programs by reducing the amount of rework due to engineering changes.
by Mark J. Davis.
S.M.
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Han, Shin-Chan. "Efficient global gravity field determination from satellite-to-satellite tracking." Columbus, Ohio : Ohio State University, 2003. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1061995200.
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Thesis (Ph. D.)--Ohio State University, 2003.Title from first page of PDF file. Document formatted into pages; contains xvii, 198 p.; also includes graphics (some col.). Includes abstract and vita. Advisor: Christopher Jekeli, Dept. of Geodetic Science and Surveying. Includes bibliographical references (p. 192-198).
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Edwards, David J. "Tracking systems for satellite communications." Thesis, University of Bristol, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.379579.
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Hultberg, Johanna. "Dehazing of Satellite Images." Thesis, Linköpings universitet, Datorseende, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-148044.
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The aim of this work is to find a method for removing haze from satellite imagery. This is done by taking two algorithms developed for images taken from the sur- face of the earth and adapting them for satellite images. The two algorithms are Single Image Haze Removal Using Dark Channel Prior by He et al. and Color Im- age Dehazing Using the Near-Infrared by Schaul et al. Both algorithms, altered to fit satellite images, plus the combination are applied on four sets of satellite images. The results are compared with each other and the unaltered images. The evaluation is both qualitative, i.e. looking at the images, and quantitative using three properties: colorfulness, contrast and saturated pixels. Both the qualitative and the quantitative evaluation determined that using only the altered version of Dark Channel Prior gives the result with the least amount of haze and whose colors look most like reality.
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Descalzi, Doug. "System design of a satellite radio frequency interference analysis system." Master's thesis, Virginia Tech, 1996. http://hdl.handle.net/10919/41244.
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see documentThe conceptual and preliminary design of the Dynamic Link Tool (DLTool) System are presented. The DLTool System performs moderate fidelity, satellite radio frequency (RF) interference and communications analysis. The primary customer of the DLTool System is Program 607 of Lockheed Martin Corporation (LMC) in Valley Forge, Pennsylvania. The system will dramatically improve the existing satellite RF interference analysis capabilities of Program 607, which are currently inadequate. Most-importantly, the DLTool System will reduce the required analysis time for satellite RF interference problems from approximately 6 hours to 1 hour. The DLTool System is intended to provide the capability to quickly predict or anticipate potential periods of RF interference. The design of the DLTool System includes an analysis of the needs of the customer, a feasibility study, the definition and allocation of operational and maintenance requirements, and the functional analysis of the system. The system is designed for a workstation-based local area network with simultaneous users, and includes a graphical user interface for input and output. The core component of the DLTool System is customized c++ code that performs the computational analysis of user defined satellite-ground station scenarios. The primary users of the system are communication engineers who will use the DLTool System to study RF interference issues for their customer.
Master of Science
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Descalzi, Douglas Hall. "System design of a satellite radio frequency interference analysis system /." This resource online, 1996. http://scholar.lib.vt.edu/theses/available/etd-02232010-020027/.
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Belguzhanov, Rustem. "Preliminary system design of the modular satellite." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2019.
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The main scope of the present thesis centres around two key points: modular block and binding interface of 4 types (mechanical/electrical/data/thermal). Throughout
the development process, the preliminary design of the modular block and mechanical interface was continuously modified, that eventually evolved into the micro-satellite
platform of different unit sizes for various mission applications. Similar to CubeSat platforms, it opens perspectives for a cheaper and faster satellite deployment by means of modularization and standardization of future satellite systems.
The proposed design is fully analysed from different perspectives and later compared to the satellite built in accordance with the traditional approach. This gives
the assurance of the validity of the comparison due to the similar mission.
As a part of the validation process, the economic analysis was conducted for three different approaches in spacecraft design, which led to the determination of the feasibility of small-mass production and plans for the future satellite constellation.
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Prince, Castro Jonathan Castro Jonathan Prince. "A global satellite system for mobile communications /." [S.l.] : [s.n.], 1995. http://library.epfl.ch/theses/?nr=1300.
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Chiyangcabut, Sarawoot. "An analysis of a satellite surveillance system." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA362535.
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Shark, Lik. "Frame synchronisation methods for digital satellite system." Thesis, University of Central Lancashire, 1988. http://clok.uclan.ac.uk/20271/.
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The research described in this thesis was carried out in four specific areas, namely, Satellite-Switched Time-Division Multiple-Access (SSTDMA) network synchronisation, frame synchronisers, remote sensing satellite data decommutating systems, and prototype frame synchroniser implementation. In the area of SSTDMA network synchronisation, this thesis reports several new synchronisation methods based on an original on-board synchronisation concept. These new methods are shown to have some significant advantages over existing methods. Also reported is a new algorithm to determine the exact satellite position for the open-loop three ranging stations method. In the area of frame synchronisers, adaptive control strategies and post-detection processing techniques are proposed for a new form of frame synchroniser. This new frame synchroniser is shown to provide reliable and optimum frame synchronisation operation in an unpredictable noisy environment. A high-speed version of the new frame synchroniser is also proposed, and it is shown that the adaptive control strategies may be implemented using a microprocessor-based system. In the area of remote sensing satellite data decommutating systems, this thesis reports a new system. Compared with existing systems, the proposed new system offers greater flexibility and expandability, with data decommutation and distribution carried out in real-time. A prototype adaptive frame synchroniser with post-detection processing was constructed, and tested under various simulated environmental conditions. The design and hardware implementation of the prototype frame synchroniser are described. The abilities of the prototype frame synchroniser, such as various mode transition strategies, automatic polarity correction, bit slippage tolerance up to ±2 bits and a bit error rate (BER) tolerance up to 0.208, were demonstrated via a range of tests, which are described in this thesis.
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Blunt, Paul. "Advanced global navigation satellite system receiver design." Thesis, University of Surrey, 2007. http://epubs.surrey.ac.uk/842714/.
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The research described by this thesis was undertaken at a very timely moment in the development of global navigation satellite systems (GNSS). During the course of this work the signal structure of an entirely new generation of GNSS signals was been defined. The first satellites producing a new range of different coding and modulation schemes have been launched, initiating the modernisation of the American GPS and the introduction of the European Galileo system. An important aspect of the new signal structure for both GPS modernisation and Galileo is an entirely new kind of modulation called BOC (Binary Offset Carrier). Despite certain advantages this modulation comes with the notorious characteristic of a multi-peaked correlation function. In our view all known receivers, or receiver principles, have problems with this: either because the receiver is not fail safe and is potentially unreliable (the so-called bump-jumping receiver); or the multi-peaks are eliminated at the very substantial cost in much degraded accuracy. During my research under Dr Hodgart what seems to be an entirely new and original method has been developed which entirely solves the problem of tracking BOC. The problem of multi-peaks goes away and there is no loss of potential accuracy. This thesis describes in detail this invention and the first experimental results. This research was carried out at the University of Surrey under the joint supervision of Surrey Space Centre and Surrey Satellite Technology Ltd. Shortly before this work began SSTL achieved a contract to design and build the first ever test satellite (Giove- A) of the Galileo signals and technology. This research contributed to the design and manufacture of a Galileo signal generator which was flown on-board the satellite (launched December 2005). Expanding upon SSTL's existing designs this work enabled the design and creation appropriate receivers to monitor the transmissions both in ground based emulations and real live tests after launch. These designs are intended to be the core of future SSTL space receivers. This thesis describes in detail the creation of both transmitter and receiver architectures for the testing and evaluation of GNSS signals.
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Beaulieu, Martin Ronald. "Launch detection satellite system engineering error analysis." Thesis, Monterey, California. Naval Postgraduate School, 1996. http://hdl.handle.net/10945/8611.
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Approved for public release; distribution is unlimited.An orbiting detector of infrared (IR) energy may be used to detect the rocket plumes generated by ballistic missiles during the powered segment of their trajectory. By measuring angular directions of the detections over several observations, the trajectory properties, launch location, and impact area may be estimated using a nonlinear least-squares iteration procedure. observations from two or more sensors may be combined to form stereoscopic lines of sight (LOS), increasing the accuracy of the estimation algorithm. The focus of this research has been to develop a computer-model of an estimation algorithm, and determine what parameter, or combination of parameters will significantly affect on the error of the tactical parameter estimation. This model is coded in MATLAB, and generates observation data, and produces an estimate for time, position, and heading at launch, at burnout, and calculates an impact time and position. The effects of time errors, LOS measurement errors, and satellite position errors upon the estimation accuracy were then determined using analytical and Monte Carlo simulation techniques.
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Mehta, Mehul. "Power control for a mobile satellite system." Thesis, University of Southampton, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.245306.
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Barry, Richard Malan. "Design of a distributed satellite ground system." Thesis, Stellenbosch : Stellenbosch University, 2001. http://hdl.handle.net/10019.1/52180.
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Thesis (MEng)--University of Stellenbosch, 2001.ENGLISH ABSTRACT: This thesis describes the development of a distributed ground support system to be used in the small satellite program at the University of Stellenbosch. A literature study was done to determine the current trends in ground support design. These trends are presented together with an analysis of the SUNSAT groundstation software. New technologies in the field of distributed systems are discussed and used in the design of a distributed ground support system. The design centres around a servicesbased architecture where services are distributed on the network. The design is evaluated according to attributes exhibited by effective distributed systems. Certain services were implemented to demonstrate the feasibility of the design. The implementations are discussed and suggestions are made for future improvements and fields of possible further study.
AFRIKAANSE OPSOMMING: Hierdie tesis beskryf die ontwikkeling van 'n verspreide-grondstasie-sisteem vir gebruik in die Universiteit van Stellenbosch se satelliet-program. Eerstens is 'n literatuurstudie gedoen om die huidige verwikkelinge in die veld van satellietondersteuning-ontwikkeling vas te stel. Hierdie verwikkelinge word bespreek en gebruik om die SUNSAT-grondstasie sagteware te evalueer. Nuwe tegnologieë in die veld van verspreide stelsels word ondersoek en bespreek. Die ontwerp van die grondstasie is gebaseer op 'n verspreide dienste argitektuur. Die ontwerp word beskryf en geëvalueer aan die hand van kenmerke tipies van 'n effektiewe verspreide stelsel. Om die werkbaarheid van die ontwerp te toon, is sekere van die dienste geïmplimenteer, en die funksionering daarvan word bespreek. Voorstelle word ook gemaak oor moontlike toekomstige navorsing wat gedoen kan word.
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Orozco, Gina. "BASELINE COMMUNICATIONS SYSTEM FOR A SMALL SATELLITE." International Foundation for Telemetering, 2003. http://hdl.handle.net/10150/605374.
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International Telemetering Conference Proceedings / October 20-23, 2003 / Riviera Hotel and Convention Center, Las Vegas, NevadaThe NMSUSat is part of the AFRL/NASA University Nanosatellite program. The constellation will consist of a main microsatellite that will have a command link from ground and a telemetry link to ground while a picosatellite will act as a sensor reporting data to the microsatellite. Innovative command and data handling will be incorporated at low cost and greater accessibility. In this paper we present the necessary communications and control architecture for the space segment and the ground segment of the nanosatellite.
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Hagen, Christoph. "A Bluetooth based intra-satellite communication system." Thesis, Luleå tekniska universitet, Rymdteknik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-65116.
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This thesis presents a wireless communication system for intra-satellite communication based on Bluetooth Low Energy technology, which can have many benefits regarding the design and operation of satellites. The proposed design based on the nRF53832 chip from Nordic Semiconductor is described, followed by the results of several tests regarding the most important design criteria for its application in small satellites. The tested aspects include the power consumption of the wireless module in different operation modes, which is sufficiently low for the application even in small satellites. Signal strength measurements for various output power settings and obstacles show that reliable communication is possible in a satellite mockup. No packet error was detected, and latencies of less than 30 ms combined with achievable data rates between 200 and 700 kbps should be sufficient for most CubeSat satellites. Additionally, details are given to successfully integrate the chip with existing satellite subsystems. A code library is provided to simplify the communication between the modules, and a concept of a redundant system is established to increase the reliability for critical satellite subsystems. The overall assessment of the technology suggests that the presented system is suitable for in-orbit deployment with the Aalto-3 satellite (currently being developed at Aalto University), which will provide further validation of the technology.
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Ruddy, Marcus A. "Pico-Satellite Integrated System Level Test Program." DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/688.
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Testing is an integral part of a satellite’s development, requirements verification and risk mitigation efforts. A robust test program serves to verify construction, integration and assembly workmanship, ensures component, subsystem and system level functionality and reduces risk of mission or capability loss on orbit.
The objective of this thesis was to develop a detailed test program for pico-satellites with a focus on the Cal Poly CubeSat architecture. The test program established a testing baseline from which other programs or users could tailor to meet their needs. Inclusive of the test program was a detailed decomposition of discrete and derived test requirements compiled from the CubeSat and Launch Vehicle communities, military guidelines, and industry standards. The test requirements were integrated into a methodical, efficient and risk adverse test flow for verification.
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Holtzman, Wendy A. "Design of the control systems operations for the Iridium satellite system." Thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-02132009-172625/.
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Khorev, Andrey. "Hardware/Software prototyping of a miniaturized star tracker system for a nanosatellite platform." Thesis, Montpellier, 2016. http://www.theses.fr/2016MONTT248/document.
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Depuis les tous premiers jours de l'ère spatiale, les satellites artificiels ont été considérés comme un outil pour la résolution de problèmes scientifiques et pratiques, notamment dans l'astronomie, l'observation de la Terre et les télécommunications. Traditionnellement, les gros satellites artificiels, avec une masse allant de plusieurs centaines de kilogrammes jusqu'à plusieurs tonnes, ont été utilisés pour ces besoins. Un élément clef pour permettre le succès de ces missions spatiales est un contrôle précis de l'attitude du satellite. Afin d'assurer la haute précision de pointage, un système de contrôle d'attitude et d'orbite (SCAO) repose sur les données fournies par un instrument optoélectronique appelé un senseur stellaire (ou Star Tracker, ST). L'utilisation des étoiles éloignées comme points de repère permet la détermination de l'attitude du satellite avec une précision de l'ordre de la seconde d'arc. Beaucoup de travaux sur la miniaturisation des sous-systèmes des satellites artificiels ont été entrepris au court des vingt dernières années. Cela a permis à l'industrie et aux passionnés de développer et construire des satellites de quelques kilogrammes pouvant accomplir de véritables missions spatiales. Centaines de ces satellites appelés « nano-satellites » sont lancé chaque année et certains parmi eux peut être considéré comme un replacement des gros satellites. Cependant, dû à de grosses contraintes de masse et de volume définis par les standards na no-satellites, tel que lU-3U CubeSat Design Specification, l'intégration de senseur stellaire dans ces nano-satellites n'était jusqu'à présent pas possible, limitant l'application de ces plateformes. Dans ce travail, senseur stellaire est considéré comme un système composé par un module caméra et un module de traitement d'image. les solutions possibles pour chaque module sont analysées séparément dans un contexte de miniaturisation de ST par modélisation et simulation. Elles sont ensuite évaluées ensemble comme les prototypes fonctionnels dans un installation hardware-in-the-loop (Hll). Cette recherche aborde plusieurs problèmes liés à la miniaturisation d'optique de caméra et du capteur d'image à pixel actif (active pixel sensor, APS), tels que la sensibilité réduite à la lumière des étoiles et l'incertitude de position des centroïdes à cause de la distorsions et l'aberrations chromatique d'optique miniaturisée. L'évaluation dans l'installation Hll se concentre autour des performances du module de traitement et plus particulièrement sur les performances du logiciel ST dans le mode d'opération « perdu dans l'espace» ("Iost-in-space", LIS). Une contribution originale de cette recherche est un algorithme de reconnaissance d'étoiles (StarID) nommé « RING-O » développé et breveté par l'auteur. Par rapport aux autres algorithmes existants, RING-O peut facilement être adapté et ajusté à différentes caméras et plateformes de traitement. Des implémentations logicielles d'algorithme ont été effectuées sur deux prototypes, l'un basé sur smartphone et l'autre basé sur une plateforme Xilinx Zynq, afin de réaliser une analyse des goulets et d'extraire les performances du système. Optimisé pour les plateformes multi-coeurs, RING-O garantit les délais d'acquisition initiale d'attitude comparable et souvent plus petits que les délais d'acquisition déclaré par les autres développeurs de senseur stellaires européensFrom the early days of the space age, satellites were considered as a solution for many scientific and practical tasks, notably astronomy, Earth observation and telecommunication. Traditionally and to the present day, mostly large satellites with a mass from several hundred kilograms to several tons are used for these purposes. The key success factor of such space missions is a fine control of satellite’s attitude. To ensure high pointing accuracy, satellite’s attitude determination and control subsystem (ADCS) relies on precise three-dimensional attitude data provided by an opto-electronic instrument called star tracker (ST). The use of stars as reference objects allows to determine the satellite’s attitude in real time with an arc-second precision.A significant work on miniaturization of satellite subsystems carried out in the past twenty years, allows us today to build a complete satellite with a mass of only a few kilograms. An increasing number of successful nano- and picosatellite missions demonstrates constantly improving capabilities of modern miniaturized satellite platforms. However, until recently, integration of a star tracker into a nanosatellite was not possible because of a large size of the device and relatively high power consumption, and that limited possible applications of the nanosatellites. In attempt to change the situation, in the last five years about a dozen of miniature star tracker prototypes, suitable for nanosatellite platforms, were proposed by various developers. Some were successfully tested in space, yet most prototypes, including the tiniest ones, are still at the development stage.A modern star tracker is a system, that can be represented as two modules, a digital camera module and a processing module. Use of a compact camera lens and a small-size image sensor allows to significantly reduce overall mass and size of the device, and at the same time, may cause significant image quality deterioration, due to increased distortion, uncompensated spherical and chromatic aberration, lower signal-to-noise ratio (SNR) and overall lower light sensitivity of the camera module. Thus, embedded software of the processing module, responsible for pre-processing, star identification and attitude calculation, should take into account the limitations imposed by the miniaturization of the camera module. At the same time, hardware architecture of the processing module should have the capacity to perform necessary correction of the digital image in real time, and to ensure stability and expected performance of the star identification and attitude calculation routines.The goal of hardware and software prototyping of a miniature star tracker system, carried out in this work, is to evaluate various design solutions, that could be brought into the camera or into the processing module, in order to help the miniaturization of the system. Another goal is to analyze the impact of every hardware and software component on the overall performance of a miniaturized star tracker system. Among the list of star tracker characteristics, the initial attitude estimation time and the attitude output rate became the focus of the research. Current work addresses possible performance bottlenecks, that may appear on any step of star tracker operation, from capturing starlight to calculation of components of the attitude quaternion, and proposes an original solution to speed-up the star identification routine
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Mwanakatwe, Mupanga. "Design and link system of a Ka-band VSAT system for use with the Olympus satellite." Thesis, University of Surrey, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.255759.
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Liu, Langtao. "An intelligent differential GPS navigation system." Thesis, Brunel University, 1997. http://bura.brunel.ac.uk/handle/2438/5219.
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This thesis describes an Intelligent Differential GPS Navigation System developed for a PhD research project. The first part of the work was to apply differential technology to Global Positioning System to locate the current position of the user with an improved positioning accuracy. The essential part of this Differential GPS system is a Differential GPS Reference Station. This DGPS Reference Station includes a DGPS mathematical model and the corresponding algorithms, which calculates the differential correction messages. These messages are then transmitted to a mobile GPS receiver by a radio data link. By using these corrections, the mobile GPS receiver's positioning accuracy can be improved from about 100 m to 4 m. This DGPS Reference station has been used to implement system software for this research. Differential correction algorithms were modified, characteristics of system components were changed, and different digital filters were also applied at different locations to investigate the impact on system performance. Besides all these capabilities which are needed for the research purpose, this DGPS Reference Station has all the standard functions, and can be used as a standard DGPS Reference Station. The second part of the work was to combine this Differential GPS system with a suitable digital map to form a navigation system. A suitable digital map database was chosen and modified, and the content of the map was then reproduced on the mobile GPS receiver's host PC screen. This digital map, combined with the current location of the user, provides the basic navigational information for the user to reach a desired destination. To help the user further and demonstrate the potential use of the system, an intelligent route-planing algorithm that can produce the optimum route automatically was also designed. The system integration was achieved by the design of the mobile navigation unit and the combination of this mobile navigation unit with the constructed DGPS Reference Station. The final system consists of a DGPS Reference Station, a UHF radio data transmitter, a mobile GPS receiver, a digital map system, a route searching and planing algorithm and a UHF radio data receiver. Field trials were carried out to test the system static and dynamic performances. Repeated experiments showed that both the static and dynamic positioning accuracies were within the range of 4 meters. The constructed system is a prototype navigation system which incorporates the basic navigational functions. It is envisaged that this system can be directly used, or further developed to suit a special need, as required. A typical application of the system would be to guide a user to a desired destination. Other examples include: aircraft autolanding control system, car self-driving, taxi fleet control, criminal tracing and personal navigation systems.
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Thipphayathetthana, Somwang. "Model-based guidelines for user-centric satellite control software development." Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/105320.
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Thesis: S.M. in Engineering and Management, Massachusetts Institute of Technology, Engineering Systems Division, 2015.Cataloged from PDF version of thesis.
Includes bibliographical references (page 45).
Three persistent common problems in satellite ground control software used by satellite controllers are obsolescence, lack of desired features and flexibilities, and endless software bug fixing. The obsolescence problem occurs when computer and ground equipment hardware become obsolete usually after only one third into the satellite mission lifetime. The satellite ground control software needs to be updated to accommodate changes on the hardware side, requiring significant work of satellite operators to test, verify, and validate these software updates. Software updates can also result from a new software version that offers new features or just fixes some bugs. Trying to help solve these problems, an OPM model and guidelines for developing satellite ground control software have been proposed. The system makes use of a database-driven application and concepts of object-process orientation and modularity. In the new proposed framework, instead of coding each software function separately, the common base functions will be coded, and combining them in various ways will provide the different required functions. The formation and combination of these base functions will be governed by the main code, definitions, and database parameters. These design principles will make sure that the new software framework would provide satellite operators with the flexibility to create new features, and enable software developer to find bugs quicker and fix them more effectively.
by Somwang Thipphayathetthana.
S.M. in Engineering and Management
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Braasch, Michael S. "On the characterization of multipath errors in satellite-based precision approach and landing systems." Ohio : Ohio University, 1992. http://www.ohiolink.edu/etd/view.cgi?ohiou1173748635.
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Nötzel, Klaus R. "Integrated Satellite Control Center." International Foundation for Telemetering, 1995. http://hdl.handle.net/10150/611618.
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International Telemetering Conference Proceedings / October 30-November 02, 1995 / Riviera Hotel, Las Vegas, NevadaDeutsche Telekom has been operating different flight models for several years. A Satellite Control Center (SCC) was designed and installed to support the operation of the satellite systems DFS Kopernikus and TV-Sat. The DFS Kopernikus system is composed of three flight models and the satellite system TV-Sat has one flight model. The aim was to design an SCC and ground stations in a way, enabling the operation of satellites and groundstations by only two operators at the main control room. The operators are well trained but not scientifically educated. The high integrated SCC supports the operators with a state of the art man-machine-interface. Software executes all necessary tasks for spacecraft- and ground station control. Interaction in front of communication equipment is not necessary. The operation of satellites is a business with a high risk potential. This paper presents the design of a Satellite Control Center with high system availability.
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Roberts, Ellen E. "Streamlined automated logistics transmission system program management and commercial satellite systems analyses." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA366174.
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Thesis (M.S. in Systems Techology (Command, Control, and Communications)) Naval Postgraduate School, June 1999."June 1999". Thesis advisor(s): John Osmundson, Douglas Brinkley. Includes bibliographical references (p. 83-84). Also available online.
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Smith, H. Todd. "A systems engineering approach to designing a remote sensing satellite simulation system." Master's thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-02162010-020240/.
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Luciani, Daniel Patrick. "System Design and Implementation of the Virginia Tech Optical Satellite Tracking Telescope." Thesis, Virginia Tech, 2016. http://hdl.handle.net/10919/71387.
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The Virginia Tech Optical Satellite Tracking Telescope (VTOST) aims to test the feasibility of a commercial off-the-shelf (COTS) designed tracking system for Space Situational Awareness (SSA) data contribution. A novel approach is considered, combining two COTS systems, a high-powered telescope, built for astronomy purposes, and a larger field of view (FOV) camera. Using only publicly available two-line element sets (TLEs), orbital propagation accuracy degrades quickly with time from epoch and is often not accurate enough to task a high-powered, small FOV telescope. Under this experimental approach, the larger FOV camera is used to acquire and track the resident space object (RSO) and provide a real-time pointing update to allow the high-powered telescope to track the RSO and provide possible resolved imagery. VTOST is designed as a remotely taskable sensor, based on current network architecture, capable of serving as a platform for further SSA studies, including unresolved and resolved imagery analysis, network tasking, and orbit determination. Initial design considerations are based on the latest Raven class and other COTS based telescope research, including research by the Air Force Research Lab (AFRL), ExoAnalytic Solutions, and other university level telescope projects. A holistic system design, including astronomy, image processing, and tracking methods, in a low-budget environment is considered. Method comparisons and results of the system design process are presented.Master of Science
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Hellman, Hans. "Design of wire boom system for a satellite." Thesis, KTH, Rymd- och plasmafysik, 1996. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-91569.
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Broomhall, Mark A. "Development of the portable satellite laser ranging system /." Full text available, 2003. http://adt.curtin.edu.au/theses/available/adt-WCU20041207.142708.
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Gerhart, Charlotte M. "A model for communications satellite system architecture assessment." Thesis, Monterey, California. Naval Postgraduate School, 2011. http://hdl.handle.net/10945/5594.
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Approved for public release; distribution is unlimited.Communications satellite system architecture trades traditionally consider only the cost per unit of capacity provided. This selection method ignores the other requirements with which the system architectures were designed and which are critical to providing a capability to the warfighter. A survey of communications satellite systems identified five common attributes that are incorporated in the design process: communications capacity; access; interoperability; commandability; and information assurance and protection. A mathematical model was implemented to enable the analysis of communications satellite system architectures based on multiple system attributes. Utilization of the model in a hypothetical case indicates system selection can differ from the traditional solution when additional key performance attributes are considered.
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Hecker, Michael A. "An expert system for processing uncorrelated satellite tracks." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/23894.
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Cooke, Adrian (Adrian Gerard). "Rural e-mail system for the Sumbandila satellite." Thesis, Stellenbosch : Stellenbosch University, 2007. http://hdl.handle.net/10019.1/17745.
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Thesis (MScIng)--University of Stellenbosch, 2007.ENGLISH ABSTRACT: Keywords: digital signal processing, OSI layer, network protocols, embedded systems, satellite technology This thesis describes the design and implementation of a rural e-mail system for the Sumbandila satellite. The rural e-mail system was developed during a project sponsored by the Department of Communications of the South African government. The complete Open Systems Interconnect (OSI) layer structure of the protocol architecture used on the satellite hardware and software is described. The equivalent implementation of the OSI layer on the ground station hardware is given. This includes the adaptation of the soundmodem Open Source Software modem to work for the e-mail system’s OSI layer. The design of the Application Layer e-mail system is described and the implementation of this design using the Python, Korn Shell and C programming environments is also given. The procedures used to test the system for reliability and the use of a database to create detailed logs of the e-mail system is shown to have generated a reliable system that is easily maintained. A critical evaluation of the system is provided in the last chapter.
AFRIKAANSE OPSOMMING: Sleutelwoorde: Syferseinverwerking, OSI-lae, netwerkprotokolle, toegewyde stelsels, satelliettegnologie Hierdie tesis beskryf die ontwerp en implementering van ’n plattelandse e-posstelsel vir die Sumbandila satelliet. Die plattelandse e-posstelsel is ontwikkel in opdrag van die Departement van Kommunikasie van die Suid-Afrikaanse regering. Die volledige Open Systems Interconnect (OSI) laagstruktuur van die protokol-argitektuur wat in die satelliet se apparatuur en programmatuur gebruik is, word beskryf. Die ekwivalente implementering van die OSI-laag op die grondstasie-apparatuur word gegee, insluitende die aanpassing van soundmodem, ’n oopbronkode sagteware-modem. Hierdie sagteware-modem word gebruik in die e-posstelsel se fisiese laag. Die ontwerp van die toepassingslaag van die e-posstelsel word beskryf, asook die implementering van hierdie ontwerp met behulp van Python, die Korninterpreteerder en C. Die prosedures waarvolgens stelselbetroubaarheid getoets is, en die gebruik van ’n databasis om noukeurige joernale van e-postransaksies te hou, demonstreer dat ’n betroubare, onderhoubare stelsel gemplementeer is. In die laaste hoofstuk word die stelsel krities geevalueer.
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Nasta, Rodolphe. "TELECOMMUNICATION SATELLITE TELEMETRY TRACKING AND COMMAND SUB-SYSTEM." International Foundation for Telemetering, 1998. http://hdl.handle.net/10150/607355.
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International Telemetering Conference Proceedings / October 26-29, 1998 / Town & Country Resort Hotel and Convention Center, San Diego, CaliforniaThis paper gives an overview on Telemetry, Tracking and Command (TTC) sub-system that are used onboard some telecommunication satellites. Then, a description of the equipments of such a sub-system is given, together with the main performances.
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Holstein, Dennis K. "Integrated Satellite Control Open System Architecture Design Standards." International Foundation for Telemetering, 1993. http://hdl.handle.net/10150/611876.
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International Telemetering Conference Proceedings / October 25-28, 1993 / Riviera Hotel and Convention Center, Las Vegas, NevadaDesign standards defined in this paper provide the framework to implement an open system architecture to achieve the interoperability requirements for integrated satellite control directed by USCINCSPACE. Ground segment space operations that implement these standards will provide the capability to eliminate the artificial barriers between mission unique ground systems that operate in a stove-pipe manner today. Through common support equipment and advanced workstations, operator cross training will become unnecessary. To implement interoperability, it is necessary to define standard physical, electrical, and communication interfaces and protocols, so components from different manufactures will operate together. Implementation of these standards tends to build on the natural infrastructure of today's satellite operation center and maximize the reuse of common user components for satellite control, mission payload operations and force management. The infrastructure concept uniquely blends the requirements for providing a single operator the capability to perform all tasks for these missions at a single workstation. Prototypes built and tested by the Air Force have demonstrated the feasibility and payoff of this design concept.
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He, Xiaoping. "The signalling system in satellite personal communication networks." Thesis, University of Surrey, 1996. http://epubs.surrey.ac.uk/844181/.
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Recent advances in both satellite and terrestrial mobile communications technologies are now leading to the realisation of the dream of the global personal communications within a few years. Satellite systems, as a complement to terrestrial cellular systems, are introduced into the future Personal Communication Networks (S-PCN) to provide global coverage and to allow global roaming. The inter-working and the integration between the satellite and the terrestrial cellular systems (e.g. GSM system) are the key issues in developing the network architecture and designing the control functions and signalling protocols of satellite systems. This thesis focuses on the design of a satellite signalling control system. The coverage and link properties of ICO10 and LE066 satellite constellations, the representatives of low earth orbit (LEO) and medium earth orbit (MEO) satellite systems, are considered. A satellite specific network architecture is proposed to accommodate the requirements of satellite dynamics and resource control function. The physical layer of satellite signalling links are designed to cope with the specific features of LEO or MEO satellite air-interfaces. In order to overcome problems specific to LEO or MEO satellite systems and to provide call set-up control function, three important signalling protocols are proposed for the S-PCNs. The priority based fast access scheme is designed for the satellite random access channel allowing low access delay for the call set-up related access packets, even when the channel load is high. The satellite diversity based paging approach is proposed to optimize the paging performance. The modified selective re-transmission (M-SRT) and Go-Back-N (M-GBN) protocols are proposed to cope with the transaction type transmission on the dedicated control channel. Simulation results have shown siginficant improvement of the M-SRT and M-GBN protocols in call setup delay. Two protocols are also compared in the aspects of implementation complexity and call set-up performance. Finally, the integration scenarios between satellite and GSM system have been examined for S-PCN in the call handling related functions and associated signalling protocols. The GSM higher layer signalling protocols are tailored to provide the call control related functions. The optimum integration scenario is derived under the criterion of minimum modifications to the GSM higher layer signalling protocols and minimum complexities of the control functions.