Accession Number : AD0875053
Title : Test Firing of an Advanced Graphite Composite Material Throat Insert.
Descriptive Note : Technical rept.,
Corporate Author : AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
Personal Author(s) : Ellison, John R.
Report Date : JUL 1970
Pagination or Media Count : 27
Abstract : The test firing of an advanced graphite material throat insert, HRX 503-X, was conducted on the Air Force Rocket Propulsion Laboratory uncured propellant char motor. The throat insert material was installed into a test weight nozzle designed and fabricated by the Air Force. The test firing utilized a 16 percent aluminum, PBAN binder uncured solid propellant. The motor and test nozzle performed adequately, with a 600 psig, 28 second duration chamber pressure versus time trace being produced. Average nozzle insert surface regression was 0.00086 inches per second. (Author)
Descriptors : *GRAPHITE), (*ROCKET NOZZLES, (*COMPOSITE MATERIALS, GRAPHITE), CARBON FIBERS, CAPTIVE TESTS, EROSIVE BURNING.
Subject Categories : Laminates and Composite Materials
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE