Report (M.S.)--Virginia Polytechnic Institute and State University. M.S. 1991. / Vita. Abstract. Includes bibliographical references (leaves 84-88). Also available via the Internet.

Thesis (M.S.)--Auburn University, 2007. / Abstract. Vita. Includes bibliographical references.

Thesis (Ph.D.)--Boston University. / An analysis is given which treats experimental heat-transfer data obtained during flights of three V-2 rockets and two Aerobee rockets. This work was conducted largely at Boston University under Air Force Contracts W28-099-ac-395 and AF 33(615)-382. The instrumentation and rocket-flight phases extended from 1947 to 1952, while the analysis was carried out in the period from 1953 to 1955. A total of nine V-2 rockets were instrumented to some extent for the purposes of this experiment. The missiles for which data have been analyzed were chosen on the basis of best performance on the part of both instrumentation and rocket. Experimental equipment of special design was produced and installed by the Boston University group in the rockets which were launched in the White Sands area in New Mexico. Extensive field trips were required in this connection, both for the experiment on heat0transer and others in which the same group participated at the same time. The general program was one of research in physics of the upper atmosphere. Since the conclusion of the supporting contracts in October of 1954, additional consideration of the experimental results has continued on a private basis. The data obtained during the course of the present experiment were in the form of temperature variations as experienced by heat meters which were placed at selected locations over the body and fin of the rockets. The heat meters were small circular diaphragms of stainless steel which were placed flush with the rocket skin. Each diaphragm had on its central inner surface a pair of resistance thermometers made of nickel wire, with a diameter of 0.002". The thermometers were switched in sequence into a resistance bridge. One thermometer had always a higher resistance than the other, an arrangement which served two purposes. Firstly, the two values of voltage for a given temperature permited unambiguous determination of the direction in which the resistance bridge was unbalanced. Secondly, these two values of voltage were handled independently by our own instrumentation, and by the recording or telemetry devices. When two such different values of voltage were finally translated back into their equivalent temperatures, close agreement of the temperature values lent considerable support to their accuracy. When the two thermometers reported temperatures which were significantly different from each other, restraint was indicated in trusting their accuracy. Fortunately, close agreement of temperatures reported by the dual thermometers was the more usual experience. [TRUNCATED]

Thesis (M.S.)--Naval Postgraduate School, 2002. / Thesis advisor(s): Bard K. Mansager, Keith F. Snider, Scott T. Crino. Includes bibliographical references (p. 75-76). Also available online.

No description available.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1994. / Vita. Abstract. Includes bibliographical references (leaves 67-68). Also available via the Internet.

Thesis (M.S.)--Ohio University, March, 1994. / Title from PDF t.p.

Thesis (M.S. in Management)--Naval Postgraduate School, December 1990. / Thesis Advisor(s): McCaffrey, Martin J. Second Reader: Doyle, Richard B. "December 1990." Description based on title screen as viewed on March 29, 2010. DTIC Identifier(s): Special Test Equipment, Guided Missiles, Foreign Sourcing, Theses. Author(s) subject terms: Special Test Equipment, Foreign Sourcing. Includes bibliographical references (p. 72-76). Also available in print.

No description available.

A method is presented which permits the measure of nose tip recession of re-entry vehicles and advanced terminal interceptors by employing a double choked flow coolant gas system. Recession of the tip results in an increased exit flow area which reduces the total pressure of the gas in the blast tube. Measurement of the blast tube pressure and gas generator (chamber) pressure will produce an effective measurement of the nose tip recession as long as choked flow (i.e., sonic velocity) is maintained in both the tip exit area and the gas generator throat area. Governing flow equations documented in the literature are developed for double choked flow. Hypersonic wind tunnel test data are presented to verify the developed flow equations and to identify the mass flow ratios necessary to sustain double choked flow.