- About
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The Global ETD Search service is a free service for researchers
to find electronic theses and dissertations. This service is
provided by the
Networked Digital Library of Theses and Dissertations.
Our metadata is collected from universities around the world. If you manage a university/consortium/country archive and want to be added, details can be found on the NDLTD website.
Search results
Showing 1 to 10 of 340 (0.023 seconds)Spelling suggestions: "subject:"docket"" "subject:"hocket""
| 1 |
Flow field investigation in pulse 1 motor of a two-pulse solid rocket motor /Qian, Xin, January 1990 (has links)
Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1990. / Vita. Abstract. Includes bibliographical references (leaves 49-50). Also available via the Internet.
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| 2 |
3-D flow and performance of a rocket pump inducer at design and off-design flow rates /Doan, Andrew W., January 1994 (has links)
Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1994. / Vita. Abstract. Includes bibliographical references (leaves 92-93). Also available via the Internet.
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| 3 |
Quasi-optimal steady state and transient maneuvers with and without thrust vectoring /Dwyer, Michael E., January 1993 (has links)
Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaves 45-46). Also available via the Internet.
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| 4 |
Experimental method of analyzing stress intensity factors and singularity order in rocket motor geometry /Che-way, Chang, January 1990 (has links)
Thesis (Ph. D.)--Virginia Polytechnic Institute and State University, 1990. / Vita. Abstract. Includes bibliographical references (leaves 128-132). Also available via the Internet.
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| 5 |
Development of a Rocket Motor Test System and a Study of Hybrid Rocket Fuel GrainsPatterson, William Ray 08 August 2009 (has links)
A rocket test system was developed and fabricated for the purpose of testing hybrid rocket motors. The test system includes a rocket test stand, load cell, and data acquisition system that is capable of safely and accurately recording thrust data from each burn. This paper documents the test system design and operation. The test system has been used to study the performance results from using multiple types of fuel utilized in hybrid motor systems. The types of hybrid motors used typically have thrust values below 1000 lbf. Along with different fuels, different motor configurations were also used during testing to determine if each hybrid rocket fuel reacted similarly under altering conditions.
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| 6 |
Design and testing of a gas distribution method for pulsed inductive thrusterMiller, Robert E. Hartfield, Roy J., January 2008 (has links)
Thesis--Auburn University, 2008. / Abstract. Vita. Includes bibliographical references (p. 52-53).
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| 7 |
Some factors affecting the stability and compatibility of propellant hydrazinesMagied, Hassan Ahmed Abdel January 1993 (has links)
No description available.
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| 8 |
Nitrato-complexes of some tri- and tetravalent metalsHowick, Christopher J. January 1989 (has links)
No description available.
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| 9 |
Structural analysis of fibre-reinforced metallic rocketmotor casesGroves, A. January 1985 (has links)
No description available.
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| 10 |
Thrust vectoring experiments with gas injectionSekhon, Kalwant Singh, 1938- January 1964 (has links)
No description available.
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