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
Pages
56 p.
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
STARS Citation
Brown, James Anthony, "Nose Tip Recession Measuring System for Hypersonic Test Vehicles" (1977). Retrospective Theses and Dissertations. 324.
https://stars.library.ucf.edu/rtd/324
Contributor (Linked data)
University of Central Florida. College of Engineering [VIAF]
Collection (Linked data)
Accessibility Status
Searchable text