Accession Number : AD0804269
Title : COMBUSTION TERMINATION SYSTEM FOR 120-INCH-DIAMETER SOLID ROCKET MOTOR (TITAN III-C).
Descriptive Note : Final rept. 1 Jul 65-30 Sep 66,
Corporate Author : UNITED TECHNOLOGY CENTER SUNNYVALE CALIF
Personal Author(s) : Nielsen,F. B.
Report Date : OCT 1966
Pagination or Media Count : 190
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.
Descriptors : (*SOLID PROPELLANT ROCKET ENGINES, *THRUST TERMINATION SYSTEMS), (*COMBUSTION, QUENCHING(INHIBITION)), ACRYLONITRILE POLYMERS, AMMONIUM PERCHLORATE, ALUMINUM, BUTYL RUBBER, HEAT TRANSFER, WATER INJECTION, INJECTORS, INJECTION, PRESSURE
Subject Categories : Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE