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Accession Number:
AD0804269
Title:
COMBUSTION TERMINATION SYSTEM FOR 120-INCH-DIAMETER SOLID ROCKET MOTOR (TITAN III-C).
Corporate Author:
UNITED TECHNOLOGY CENTER SUNNYVALE CALIF
Report Date:
1966-10-01
Abstract:
As a result of these tests, it was established that solid propellant motors cast with PBAN polybutadiene acrylonitrile propellant could be extinguished by injecting a liquid into the compustion chamber. The mechanism controlling the extinguishment of PBAN was determined to be heat transfer. For this reson, water, with its high specific heat, proved to be the most effective injectant, and the necessity of contacting all burning surfaces by the injectant was established. Radial slots in the propellant charge downstream of the injector were found to be particularly difficult to contact with injectant and were therefore subject to reignition. For this reason, a reliable system for extinguishing the Titan III-C was not developed.
Descriptive Note:
Final rept. 1 Jul 65-30 Sep 66,
Supplementary Note:
DOI: 10.21236/AD0804269
Pages:
0190
Contract Number:
AF 04(695)-845
File Size:
126.64MB
