Accession Number : AD0476521
Title : COMBUSTION TERMINATION SYSTEM FOR 120-INCH-DIAMETER SOLID ROCKET MOTOR (TITAN III-C).
Descriptive Note : Quarterly progress rept. 1 Jul-1 Oct 65,
Corporate Author : UNITED TECHNOLOGY CENTER SUNNYVALE CALIF
Personal Author(s) : Nelson,F. B.
Report Date : DEC 1965
Pagination or Media Count : 42
Abstract : An investigation was made of combustion termination of solid propellant motors by liquid injection. The program consists of four tasks, which include laboratory and small-motor testing, subscale testing, and system demonstration in a 120-in.-diameter solid-propellant motor. A total of 4 laboratory motor and 19 small-motor (TM-1) tests were performed to evaluate several injection systems and to provide data for the study of the fundamental phenomena of combustion termination by liquid injection. In addition, 22 laboratory cold flow tests were conducted to evaluate injector flow patterns. As a result of these tests, a pintle-type injector was selected for further evaluation in the subscale (TM-3A) motor firings. Data obtained during the test program have been analyzed, and a correlation between the requirements of water flow rate and total water quantity and the motor ballistic properties was established. (Author)
Descriptors : (*SOLID PROPELLANT ROCKET ENGINES, *THRUST TERMINATION SYSTEMS), COMBUSTION, LAUNCH VEHICLES, SCHEDULING, IGNITION, PROPAGATION, CAPTIVE TESTS, INJECTORS, SPRAYS, SEGMENTED ROCKET ENGINES, LIQUIDS, COLD FLOW
Subject Categories : SOLID PROPELLANT ROCKET ENGINES
Distribution Statement : APPROVED FOR PUBLIC RELEASE