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Accession Number:
AD0607223
Title:
SOLID-PROPELLANT ROCKET IGNITION RESEARCH.
Corporate Author:
NAVAL ORDNANCE LAB WHITE OAK MD
Report Date:
1964-07-22
Abstract:
A theoretical and experimental study was made of solid rocket ignition for the purpose of obtaining igniter design criteria. Heat-transfer, ballistic, and ignition data were obtained by firing a rocket-type igniter, venting noncondensable products at an unsteady rate, into a small rocket. Measurements were made of igniter and rocket pressures, grain surface temperatures, and ignition times. In the tests, the heat fluxes ranged from 19 to 48 calsq. cm.-sec and ignition times from .002 to .015 sec. It was found that the ignition test data were in fair agreement to those predicted from the von Elbe ignition theory. An igniter design method, developed from test data and the von Elbe theory, is described. Author
Descriptive Note:
Final rept.,
Pages:
0136
File Size:
0.00MB
