Combustion Termination System for 120-Inch-Diameter Solid Rocket Motor (Titan III-C)

摘要

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)