Accession Number : AD0739881
Title : Thermal Performance of a Gimbaled Supported, Onmidirectional Supersonic Split-Line Nozzle.
Descriptive Note : Technical rept. Jan 70-Dec 71,
Corporate Author : AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CALIF
Personal Author(s) : Holder,R. W.
Report Date : MAR 1972
Pagination or Media Count : 34
Abstract : An analysis of the erosion and char performance of a 2.6-inch-throat-diameter supersonic split-line nozzle exposed to a 650 psi chamber pressure solid propellant motor environment for 35 seconds was conducted. The nozzle was a lightweight nozzle design employing pyrolytic graphite washers in the throat with Graph-I-Tite G graphite on either side. Grafoil 101, graphite cloth phenolic and silica phenolic were used to insulate the 7075-T6 aluminum nozzle shell. The exit cone was reinforced with a fiberglass overwrap. The nozzle successfully demonstrated a 4-degree pitch and yaw capability. The pyrolytic graphite slates eroded at a rate of 0.76 mil per second in the throat plane. (Author)
Descriptors : (*MOVABLE NOZZLES, THERMAL ANALYSIS), (*SOLID PROPELLANT ROCKET ENGINES, *THRUST VECTOR CONTROL SYSTEMS), SUPERSONIC NOZZLES, NOZZLE THROATS, NOZZLE AREA RATIO, PYROLYTIC GRAPHITE, SPECIFIC HEAT, CAPTIVE TESTS, EROSIVE BURNING
Subject Categories : Rocket Engines
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE