Abstract
Thirty-four different ceramic materlals were evaluated as nozzle liners in a laboratory rocket motor employing oxygen and hydrogen as the propellants. The motor was operated with a four-to-one volume ratio of H/sub 2/ and 0/sub 2/ and with a chamber pressure of 200 psia, giving a combustion temperature of about 4500 F. The speclflc impulse was about 265 seconds. Under these conditions, of the materials tried, ceramics of silicon carbide, zirconium boride, or beryllia, and a sillconimpregnated graphite were affected least. Functional life of the motor with the various experimental nozzles ranged from less than 15 to 107 seconds. A classification of the nozzle materials according to thelr functional life is given. Additional tests using dlfferent operating conditions in the test motor are recommended for firm conclusions on the merits of the materials as rocket liners. (auth)
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