Thermal Performance of a Gimbaled Supported, Onmidirectional Supersonic Split-Line Nozzle.
Technical rept. Jan 70-Dec 71,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CALIF
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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
- Rocket Engines
- Solid Propellant Rocket Engines