Initial objectives of this work were to develop a high temperature resistant material capable of withstanding rocket nozzle throat, leading edge, or re-entry environments by virtue of its high temperature strength, resistance to oxidation, and ability to cool itself ablatively. (Author)
High Viscosity Thermal Protection Materials
1969
63 pages
Report
No indication
English
Rocket Engines & Motors , Iron & Iron Alloys , Rocket engines , Nozzle inserts , Nozzle throats , Heat resistant alloys , High temperature , Tungsten alloys , Composite materials , Silicon alloys , Powder metallurgy , Compacting , Sintering , Mechanical properties , Particle size , Temperature , Measurement
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