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