The applicability of cast-extruded-forged tungsten throat inserts for solid propellant rocket nozzles was demonstrated. Inserts were prepared to conventional designs from tungsten forgings produced during a previous MATB development program. Instrumented nozzles containing the inserts were assembled and were test fired at the Rocket Propulsion Laboratory (RPL), Edwards Air Force Base. RPL Liquids Division (Alumizine propellant) and Solids Division (solid propellant) test stands were employed for the test firings. Subsequent evaluation revealed that the tungsten inserts were incompatible with the Alumizine propellant environment, and that they performed effectively in maintaining nozzle throat dimensions for long duration firings with solid propellants. Graphitic and plastic-silica laminate nozzle components were also evaluated. Erosion and insulation data obtained from these components are reported. (Author)
Tungsten Insert Firing Evaluation
1966
75 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Iron & Iron Alloys , Nozzle inserts , Tungsten alloys , Captive tests , Performance(Engineering) , Forging , Extrusion , Casting , Solid propellant rocket engines , Liquid propellant rocket engines , Graphite , Composite materials , Thermal insulation , Erosion , Tungsten alloy 2mo
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