Keywords

Guided missiles, Design and construction

Abstract

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.

Graduation Date

1977

Advisor

Evans, Ronald D.

Degree

Master of Science (M.S.)

College

College of Engineering

Degree Program

Engineering

Format

PDF

Pages

x, 56 pages

Language

English

Rights

Written permission granted by copyright holder to the University of Central Florida Libraries to digitize and distribute for nonprofit, educational purposes.

Length of Campus-only Access

None

Access Status

Masters Thesis (Open Access)

Identifier

DP0003483

Subjects

Guided missiles -- Design and construction

Collection (Linked data)

Retrospective Theses and Dissertations

Included in

Engineering Commons

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