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):

Report Date:

1972-03-01

Pagination or Media Count:

34.0

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

Subject Categories:

  • Rocket Engines
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE