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Dissertations / Theses on the topic 'Launch vehicles (Astronautics) Space vehicles'

Author: Grafiati

Published: 4 June 2021

Last updated: 13 February 2022

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1

Bayley, Douglas James. "Design optimization of space launch vehicles using a genetic algorithm." Auburn, Ala., 2007. http://repo.lib.auburn.edu/2007%20Spring%20Dissertations/BAYLEY_DOUGLAS_5.pdf.

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2

Vissepó, Varlin. "Reusable launch vehicles : crossroads between air and space law." Thesis, McGill University, 2003. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=81239.

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Space technology is increasingly becoming part of our everyday life, businesses, governments and private entities rely heavily on satellite communications for their respective dealings and transactions. On the other hand, not all transactions or businesses can be done solely through telecommunications, we often need to get on an airplane and go somewhere else to do our respective businesses and if we are on vacation we definitely need to travel. The problem is that airplane travel, although fast, sometimes is not fast enough. Today's people want convenience and when they want something

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3

Good, Marissa Ann. "Developing a component reuse strategy for space launch vehicles." Thesis, Massachusetts Institute of Technology, 2017. http://hdl.handle.net/1721.1/112486.

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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, 2017.<br>Thesis: M.B.A., Massachusetts Institute of Technology, Sloan School of Management, in conjunction with the Leaders for Global Operations Program at MIT, 2017.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (page 84).<br>Launch vehicle hardware is traditionally very expensive to design, develop, produce and certify, because it must operate in extreme environments with high reliability. The

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4

Winter, Tyler Forrest. "Analysis of access-to-space missions utilizing on-board energy management and entropic analysis." Diss., Rolla, Mo. : Missouri University of Science and Technology, 2008. http://scholarsmine.mst.edu/thesis/pdf/Winter_09007dcc804d07b4.pdf.

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Thesis (M.S.)--Missouri University of Science and Technology, 2008.<br>Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed April 18, 2008) Includes bibliographical references (p. 127-129).

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5

Steffens, Michael J. "A combined global and local methodology for launch vehicle trajectory design-space exploration and optimization." Thesis, Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/51884.

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Trajectory optimization is an important part of launch vehicle design and operation. With the high costs of launching payload into orbit, every pound that can be saved increases affordability. One way to save weight in launch vehicle design and operation is by optimizing the ascent trajectory. Launch vehicle trajectory optimization is a field that has been studied since the 1950’s. Originally, analytic solutions were sought because computers were slow and inefficient. With the advent of computers, however, different algorithms were developed for the purpose of trajectory optimization. Computer

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6

Cowart, Karl K. "A method for integrating aeroheating into conceptual reuable launch vehicle design." Thesis, Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/12339.

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7

Schlegelmilch, Barret William. "A framework for safe system design in space launch vehicles." Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/117986.

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Thesis: M.B.A., Massachusetts Institute of Technology, Sloan School of Management, in conjunction with the Leaders for Global Operations Program at MIT, 2018.<br>Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, in conjunction with the Leaders for Global Operations Program at MIT, 2018.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (page 65).<br>A hazard analysis for the test firing of NASA's Space Launch System core stage is performed using a systems-based alternative to the traditional reliability-based method.

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8

Thessin, Rachel Neville. "Atmospheric signal delay affecting GPS measurements made by space vehicles during launch, orbit and reentry." Thesis, Massachusetts Institute of Technology, 2005. http://hdl.handle.net/1721.1/33211.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2005.<br>This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.<br>Includes bibliographical references (p. 179-182).<br>In this thesis, I present neutral atmosphere, ionosphere and total delays experienced by GPS signals traveling to space vehicles during launch, orbit and reentry. I calculate these delays for receivers at 0 km to 1700 km altitude by ray-tracing through the Global Reference Atmosphere Model (199

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9

Kayser, Valérie. "Liability risk management for activities related to the launch of space objects : today's environment and tomorrow's prospects." Thesis, McGill University, 2000. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=37742.

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Launch activities are increasingly performed by private entities and launch participants deal with a complex legal environment. The Space Treaties provide a framework placing liability for non-governmental activities on the launching State and the duty to authorize and supervise them on the appropriate State. Launch participants are subject to specific regulation in certain States or are under institutional State control in others. They also have to comply with general domestic law of liability. Limited insurance availability led to the development of contractual risk allocation techniques, th

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10

Fiallos, Pazmiño Luis Fernando. "Legal aspects of launching and operating spacecraft." Thesis, McGill University, 2003. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=80919.

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Over the last years, the number of commercial space activities has increased tremendously. Technological developments have been the main reason in the emerging of new services that use space infrastructure. In order to provide these new space services, it is necessary to launch and operate spacecraft.<br>Complying with the laws and regulations of the launching and operating activities is one of the most relevant issues that prospective spacecraft operators may face in this complex industry.<br>This work compiles the legal sources to effectively launch and operate spacecraft destined for

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11

Hermida, Julian. "Legal aspects of space risk management : the allocation of risks and assignment of liability in commercial launch services." Thesis, McGill University, 2000. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=33357.

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This thesis examines the way legal space risks are managed in commercial space transportation provided by major carriers, such as, NASA, the US private launch sector, and Arianespace, as well as in the system envisaged for Australia. Its purpose is to show that even if all systems tend to provide a favorable risk allocation scheme to the space launch industry, there are several alternatives for the telecommunications satellite operators. It also attempts to show that, even if all these risk sharing regimes have been modeled after NASA's, there are certain important differences, which stem from

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12

Johnson, Eric N. "Limited authority adaptive flight control." Diss., Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/12953.

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13

Mugarra, Leire. "Legal aspects of commercial space transportation." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112607.

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The commercial space transportation industry is growing with the technology that creates more capable spacecrafts to access space. However, there are still some academic discussions related to the delimitation of the outer space and the definition of space objects that could interfere with the regulation of this growing space activity. Because these discussions are not predicted to be solved soon, the developing space policies must attempt to clarify these issues between the parts avoiding the retard in the development of the industry. Moreover, these policies have to promote public-private pa

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14

Mantis, George C. "Quantification and propagation of disciplinary uncertainty via bayesian statistics." Diss., Georgia Institute of Technology, 2002. http://hdl.handle.net/1853/12136.

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15

Francis, Richard J. (Richard James) 1974. "A systems study of very small launch vehicles." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/9383.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.<br>Includes bibliographical references (p. 111-115).<br>Motivated by the continuing miniaturization of small satellites and ballistic payloads, this thesis studies the perform&ace and feasibility of very small launch vehicles (15 kg- 2000 kg liftoff mass). Gross payload performance for several vehicles was calculated with a commercial three degree of freedom trajectory code. The significance of aerodynamic drag on small vehicles is discussed. Both the options of air and ground-launched vehicles w

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16

McDavid, Brian Robert Hartfield Roy J. "Launch vehicle performance enhancement using aerodynamic assist." Auburn, Ala, 2008. http://repo.lib.auburn.edu/EtdRoot/2008/SUMMER/Aerospace_Engineering/Thesis/Mcdavid_Brian_9.pdf.

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17

Munson, Jeffrey Eric 1974. "The impact of launch vehicle constraints on space system design." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/82210.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics; and, (S.M.)--Massachusetts Institute of Technology, Technology and Policy Program, 2001.<br>Includes bibliographical references (p. 163-166).<br>by Jeffrey Eric Munson.<br>S.M.

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18

Comstock, Douglas Allen. "Enhancing the orbital utilization of expendable launch vehicles." Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/34040.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1988, and (M.S.)--Massachusetts Institute of Technology, Technology and Policy, 1988.<br>Vita.<br>Includes bibliographical references.<br>by Douglas Allen Comstock.<br>M.S.

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19

Tracy, Chisholm C. (Chisholm Cain) 1975. "Integrated entry guidance and control for autonomous reusable launch vehicles." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/8790.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.<br>Includes bibliographical references (p. 163-164).<br>The guidance and control approach employed on current reusable launch vehicles is based on classical control techniques developed for the Space Shuttle more than 20 years ago. This approach partitions the guidance and control tasks into separate loops resulting in a complex control architecture that can be difficult to adapt to new vehicle designs. A new entry guidance and control technique based on time-invariant linear quadratic regulator

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20

Khan, Kashif A. "Air traffic management and conflict analysis for reusable launch vehicles." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/50473.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998.<br>Includes bibliographical references (leaf 75).<br>Increasing demand for commercial utilization of space is accelerating the development of technologies that have the potential of providing safer and more economical access to space. Reusable Launch Vehicles (RLVs) are expected to take over a significant portion of the launch markets. Increased utilization of Spaceports will increase the frequency of interruptions to normal airspace operations and new methods of Aircraft-RLV separation need to b

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21

Rising, John M. (John Michael). "Safety-guided design & analysis of space launch vehicles." Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/118525.

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Thesis: S.M. in Engineering and Management, Massachusetts Institute of Technology, System Design and Management Program, 2018.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 103-108).<br>The advent of commercial launch systems has brought about a new age of space launch vehicle design. In order to survive in a competitive market, space launch providers must design systems with new technologies in shorter development times. This changing nature of space launch vehicle design requires a new way to perform safety analysis. Traditional hazard analysis techni

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22

Bevacqua, Timothy R. "Advanced Flight Control Issues for Reusable Launch Vehicles." Ohio University / OhioLINK, 2004. http://www.ohiolink.edu/etd/view.cgi?ohiou1097601560.

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23

Bizzarri, Didier. "Compact air separation system for space launcher." Doctoral thesis, Universite Libre de Bruxelles, 2008. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210488.

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A compact air separator demonstrator based on centrifugally enhanced distillation has been studied. The full size device is meant to be used on board of a Two Stage To Orbit vehicle launcher. The air separation system must be able to extract oxygen in highly concentrated liquid form (LEA, Liquid Enriched Air) from atmospheric air. The LEA is stored before being used in a subsequent rocket propulsion phase by the second stage of the launcher. Two reference vehicles are defined, one with a subsonic first stage and one with a supersonic first stage. In both cases, oxygen collection is performed d

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24

Shaffer, Patrick J. "Optimal trajectory reconfiguration and retargeting for the X-33 reusable launch vehicle." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Sep%5FShaffer.pdf.

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25

Girerd, André R. (André René) 1977. "Onboard trajectory generation for the unpowered landing of autonomous Reusable Launch Vehicles." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/8713.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2001.<br>Includes bibliographical references (p. 167-168).<br>Onboard trajectory generation dispenses with the pre-defined trajectories used. in Reusable Launch Vehicle (RLV) guidance since the early days of the Shuttle era. This shift, enabled by a new breed of algorithms harnessing modern computer power, offers improvements in performance, robustness, operational cost, and safety. This thesis develops a set of algorithms providing onboard trajectory generation for low lift-over-drag gliding RLVs in s

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26

Su, Shelly. "Advanced guidance algorithms for the Ares V cargo launch vehicle." Diss., Columbia, Mo. : University of Missouri-Columbia, 2008. http://hdl.handle.net/10355/5648.

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Thesis (M.S.)--University of Missouri-Columbia, 2008.<br>The entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. Title from title screen of research.pdf file (viewed on August 17, 2009) Includes bibliographical references.

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27

Schafer, Michael D. "Feasibility of SCRAMJET technology for an intermediate propulsive stage of an expendable launch vehicle." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02sep%5FSchafer.pdf.

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Thesis (M.S. in Space Systems Operations)--Naval Postgraduate School, September 2002.<br>Thesis advisor(s): Stephen A. Whitmore, Charles M. Racoosin. Includes bibliographical references (p. 93). Also available online.

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28

Craft, Jason Scott. "Evaluation of advanced titanium matrix composites for 3rd generation reusable launch vehicles." Thesis, Georgia Institute of Technology, 2003. http://hdl.handle.net/1853/17644.

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29

Roper, Benjamin F. Newberry Conrad F. "Exergy decrease in shock waves and boundary layers of space launch vehicles /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School; Available from the National Technical Information Service, 1993. http://handle.dtic.mil/100.2/ADA265272.

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Thesis (M.S. in Systems Technology (Space Systems Operations) and M.S. in Engineering Science) Naval Postgraduate School, March 1993.<br>Thesis advisor(s): Conrad F. Newberry. "March 1993." Includes bibliographical references. Also available online. Mode of access: World Wide Web.

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30

Roper, Benjamin F. "Exergy decrease in shock waves and boundary layers of space launch vehicles." Thesis, Monterey, California. Naval Postgraduate School, 1993. http://hdl.handle.net/10945/39889.

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The exergy method of analysis uses both the First and Second laws of Thermodynamics to determine where losses occur. This method has been shown to be superior to conventional heat balance analyzes. A primary contributor to the exergy decrease is the production of entropy. Entropy is produced in shock waves and boundary layers, as well as in other regions of the flowfield. A method of analysis is presented to quantify the entropy that is produced in the bow shock wave and the boundary layer of a space launch vehicle for Mach numbers between 1.1 and 10. Exergy,

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31

Cinniger, Anna Gibbs. "Control for interfaces and handling qualities for space telerobotic vehicles." Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/42494.

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32

Bradford, John Edward. "A technique for rapid prediction of aftbody nozzle performance for hypersonic launch vehicle design." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12896.

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33

Grubler, Andrew C. (Andrew Clay) 1976. "New methodologies for onboard generation of Terminal Area Energy Management trajectories for autonomous reusable launch vehicles." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/8712.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2001.<br>Includes bibliographical references (p. 144-145).<br>Onboard trajectory generation capability greatly increases an autonomous reusable launch vehicle's capacity for recovering from unexpected disturbances or anomalous conditions. Such capability dispenses with the routine of pre-defined, mission specific trajectories and contingencies, which has been in use since the early days of the Shuttle. Newer guidance techniques, employing modem computing power and faster algorithms, can therefore provi

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34

Friedrich, Linus [Verfasser]. "Towards Robust Design Concepts for Shell Structures of Space Launch Vehicles / Linus Friedrich." Aachen : Shaker, 2016. http://d-nb.info/1118259343/34.

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35

Bless, Robert R. "Time-domain finite elements in optimal control with application to launch-vehicle guidance." Diss., Georgia Institute of Technology, 1991. http://hdl.handle.net/1853/20211.

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36

Allport, Christopher Samuel. "Mission planning and remote operated vehicle simulation in a virtual reality interface." Morgantown, W. Va. : [West Virginia University Libraries], 1999. http://etd.wvu.edu/templates/showETD.cfm?recnum=635.

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Thesis (M.S.)--West Virginia University, 1999.<br>Title from document title page. Document formatted into pages; contains vii, 122 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 38-39).

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37

Tappe, Jack A. "Development of star tracker system for accurate estimation of spacecraft attitude." Thesis, Monterey, California : Naval Postgraduate School, 2009. http://edocs.nps.edu/npspubs/scholarly/theses/2009/Dec/09Dec%5FTappe.pdf.

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Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, December 2009.<br>Thesis Advisor(s): Kim, Jae Jim ; Agrawal, Brij N. "December 2009." Description based on title screen as viewed on January 26, 2010. Author(s) subject terms: Star tracker, Planar triangles, Angle method, Spherical triangle, Quaternion estimator, Least-squares (QUEST), TRIAD Includes bibliographical references (p. 87-88). Also available in print.

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38

O'Brien, Patrick Charles. "Challenges and methodology in the design of a vertical lift aerial vehicle for use on the planet Mars." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12017.

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39

McDonald, Paul Charles. "Cryogenically cooled amplifiers for deep space communication." Thesis, University of Southampton, 2001. https://eprints.soton.ac.uk/35405/.

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40

McCormick, David Jeremy. "Distributed uncertainty analysis techniques for conceptual launch vehicle design." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12892.

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41

Denton, Brandon Lee. "Design and analysis of rocket nozzle contours for launching pico-satellites /." Online version of thesis, 2008. http://hdl.handle.net/1850/6003.

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42

White, Adam Edward. "An adaptive strategy to control the space debris population." Thesis, University of Southampton, 2014. https://eprints.soton.ac.uk/377012/.

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As a result of the last 60 years of satellite launches, a significant amount of space debris has been generated in Earth orbit. Growing consensus amongst experts over the last decade, has suggested that removing existing debris, alongside mitigation efforts, can assist in controlling the size of the low Earth orbit (LEO) population. However, no objective or long-term strategy exist to ensure the most effective use of active debris removal (ADR). The way we utilise near-Earth space, and the way the space environment will behave in the future will directly affect the number of debris objects req

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43

Tiffin, Daniel Joseph. "Orbital Fueling Architectures Leveraging Commercial Launch Vehicles for More Affordable Human Exploration." Case Western Reserve University School of Graduate Studies / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=case1575590285930015.

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44

Dunnett, Oliver. "The British Interplanetary Society and cultures of outer space, 1930-1970." Thesis, University of Nottingham, 2011. http://etheses.nottingham.ac.uk/2403/.

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This thesis explores the institutional and cultural development of the British Interplanetary Society (BIS) and its influence in wider cultures of ‘British outer space’ in the mid-twentieth century. The Society was founded in 1933 in Liverpool by P E Cleator, and having attracted a small group of enthusiastic members before the outbreak of the Second World War, successfully re-grouped after the conflict and grew to become one of the most influential of all the space flight societies by the 1960s. The thesis starts by examining the ways in which the discipline of geography has recently started

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45

Thomson, Grace. "A multi-wavelength, Hubble space telescope study of two globular clusters." Thesis, University of Southampton, 2013. https://eprints.soton.ac.uk/349262/.

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Globular clusters (GCs) are among the densest and oldest stellar aggregates in the Galaxy, and are thought to date from around the time that the Galaxy first formed. The high central densities that characterise GCs lead to frequent stellar interactions and the formation of exotic stellar populations, making GCs excellent laboratories for studying the stellar dynamics of dense environments. The ability to observe many stars which are equidistant and (approximately) the same age makes GCs invaluable in understanding stellar structure and evolution. This thesis describes surveys of two Galactic G

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46

Amy, Robin A. "Efficient design of spacecraft electronics to satisfy launch vibration requirements." Thesis, University of Southampton, 2009. https://eprints.soton.ac.uk/73512/.

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This work proposes three tools that improve the spacecraft electronic equipment design process, where these tools reduce the chance of the equipment failing the pre-flight qualification vibration test, whilst also being quick and simple to implement. These relatively simple tools consist of: (1) a list of different component types ordered by their ability to withstand vibration, allowing a user to choose more robust packages over weaker ones; (2) simple maps that roughly show the magnitude of the vibration response over the PCB (Printed Circuit Board), allowing the more sensitive components to

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47

Gordon, Kayleigh Elizabeth. "Analysis of Chinese Cryogenic Long March Launch Vehicles and YF-100 Liquid Rocket Engine." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1524154852226897.

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48

Croisard, Nicolas. "Reliable preliminary space mission design : optimisation under uncertainties in the frame of evidence theory." Thesis, University of Glasgow, 2013. http://theses.gla.ac.uk/4008/.

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In the early phase of the design of a space mission it is generally desirable to investigate as many feasible alternative solutions as possible. Traditionally a system margin approach is used in order to estimate the correct value of subsystem budgets. While this is a consolidated and robust approach, it does not give a measure of the reliability of any of the investigated solutions. In addition the mass budget is typically overdimensioned, where a more accurate design could lead to improvements in payload mass. This study will address two principal issues typically associated with the design

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49

Dees, Patrick Daniel. "A simulation framework for the analysis of reusable launch vehicle operations and maintenance." Thesis, Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/45747.

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During development of a complex system, feasibility initially overshadows other concerns, in some cases leading to a design which may not be viable long-term. In particular for the case of Reusable Launch Vehicles, Operations&Maintenance comprises the majority of the vehicle's LCC, whose stochastic nature precludes direct analysis. Through the use of simulation, probabilistic methods can however provide estimates on the economic behavior of such a system as it evolves over time. Here the problem of operations optimization is examined through the use of discrete event simulation. The resulting

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Arslantas, Yunus Emre. "Conceptual Design Optimization Of A Nano-satellite Launcher." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614364/index.pdf.

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Recent developments in technology are changing the trend both in satellite design and application of that technology. As the number of small satellites built by experts from academia and private companies increases, more effective ways of inserting those satellites into orbit is needed. Among the various studies that focus on the launch of such small satellites, research on design of Launch Vehicle tailored for nano-satellites attracts special attention. In this thesis, Multiple Cooling Multi Objective Simulated Annealing algorithm is applied for the conceptual design of Launch vehicle for na

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