Accession Number : AD0880628
Title : Flexible Exit Cone Nozzle Firing.
Descriptive Note : Technical rept.,
Corporate Author : AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
Personal Author(s) : Ojala, Steven J. ; Ellison, John R.
Report Date : DEC 1970
Pagination or Media Count : 40
Abstract : This report describes the test firing of a thrust vector control (TVC) system on the AFRPL 40-inch-diameter char motor. The TVC system (developed under Contract F04611-68-C-0004) consisted of a movable exit cone (Flex-X) nozzle and support hardware, which was designed to combine the advantages of the elastomeric bearing with those of the supersonic splitline nozzle. The elastomeric bearing failed after 21 seconds of motor operation. Probable reasons for the failure and a general description of the preparations and motor performance are described in the text. (Author)
Descriptors : (*MOVABLE NOZZLES, CAPTIVE TESTS), (*SOLID PROPELLANT ROCKET ENGINES, THRUST VECTOR CONTROL SYSTEMS), JETAVATORS, NOZZLE CLOSURES, THERMAL ANALYSIS, TORQUE, FAILURE(MECHANICS), STATISTICAL DATA.
Subject Categories : Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE