Accession Number : AD0502017
Title : Test and Evaluation of Nozzle Insert Materials Using Fluorinated Oxidizer and Hydrazine Fuel Propellants.
Descriptive Note : Final rept. 15 Feb 67-15 Mar 69,
Corporate Author : PHILCO-FORD CORP NEWPORT BEACH CALIF AERONUTRONIC DIV
Personal Author(s) : Hale,Robert M.
Report Date : 26 MAY 1969
Pagination or Media Count : 145
Abstract : This report presents the results of a program to evaluate nozzle insert materials for use in fluorinated oxidizer hydrazine fuel rocket engines. Based on chemical, thermal and structural analyses the materials were selected and nozzles were designed to test fire the materials. Nozzles were designed to use fluorine and chlorine trifluoride (CTF) as the oxidizer. Edge oriented pyrolytic graphite, Super-Temp RPG and Union Carbide pyrolytic graphite bonded carbon felt were fired as nozzle inserts using CTF-monomethyl hydrazine propellant. All nozzles were designed on the basis of fluorine-hydrazine propellant. The three nozzles sized for the fluorine oxidizer firings were constructed but not tested.
Descriptors : (*HYDRAZINE, NOZZLE INSERTS), (*NOZZLE INSERTS, LIQUID ROCKET FUELS), LIQUID ROCKET OXIDIZERS, CHLORINE COMPOUNDS, LIQUID PROPELLANT ROCKET ENGINES, CAPTIVE TESTS, ROCKET NOZZLES, FLUORIDES, THERMAL ANALYSIS, STRUCTURAL PROPERTIES, REFRACTORY MATERIALS, HEAT RESISTANT MATERIALS, TENSILE PROPERTIES, FLUORINE COMPOUNDS, COMPRESSIVE PROPERTIES, MODULUS OF ELASTICITY (U) PYROLYTIC GRAPHITE, METHYL HYDRAZINES, NOZZLE THROATS, EROSION
Subject Categories : Rocket Engines
Liquid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE