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 cal/sq. 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)
Solid-Propellant Rocket Ignition Research
1964
2 pages
Report
No indication
English
Low Acceleration Solid Propellant Rocket Ignition Study
NTIS | 1971
|Laser initiation of solid propellant rocket ignition
NTRS | 1962
|Low acceleration solid propellant rocket ignition study
NTRS | 1971
|Ignition-Transient Modeling for Solid Propellant Rocket Motors
British Library Conference Proceedings | 2000
|The ignition transient in solid propellant rocket motors
AIAA | 1964
|