Abstract: A method for manufacturing carbon/silicon-carbide composite by a ‘One-shot’ process including carbonization, heat processing, infiltration, and forming an anti-oxidation layer on surface is provided through the steps of: 1) hardening a stacked carbon/phenolic preform; 2) carbonization and heat processing the preform until the temperature reaches at 2300° C.; 3) infiltrating and sintering the liquid metal silicon within the temperature of 1400˜1800° C.; and 4) inducting a compound including SiO2to gas phase and heat processing it while forming an anti-oxidation layer on the surface within temperature range of 2000° C.˜2700° C. (desirably, in the range of higher than 2300° C., and more desirably, at the temperature near 2500° C.). Herein, the carbonization, heat processing, and ultra-high heat processing might be performed at the same time in the step 2) and the step 4) might not be performed.

Abstract: A method for manufacturing carbon/silicon-carbide composite by a ‘One-shot’ process including carbonization, heat processing, infiltration, and forming an anti-oxidation layer on surface is provided through the steps of: 1) hardening a stacked carbon/phenolic preform; 2) carbonization and heat processing the preform until the temperature reaches at 2300° C.; 3) infiltrating and sintering the liquid metal silicon within the temperature of 1400˜1800° C.; and 4) inducting a compound including SiO2to gas phase and heat processing it while forming an anti-oxidation layer on the surface within temperature range of 2000° C.˜2700° C. (desirably, in the range of higher than 2300° C., and more desirably, at the temperature near 2500° C.). Herein, the carbonization, heat processing, and ultra-high heat processing might be performed at the same time in the step 2) and the step 4) might not be performed.

Abstract: Members for a rocket nozzle and a fabrication method thereof, wherein members for a rocket nozzle stacked in order of: a heat-resistant element; a first adhesive which is a thermosetting room temperature-hardening epoxy resin; a second adhesive which is a thermoplastic resin; a third adhesive which is a thermosetting medium temperature-hardening epoxy resin; and a structural body. The fabrication method according to the present invention comprises stacking a first adhesive, which is a thermosetting room temperature-hardening epoxy resin, on a surface of a heat-resistant element; stacking a second adhesive, which is a thermoplastic resin, on the first adhesive; stacking a third adhesive which is a thermosetting medium temperature-hardening epoxy resin, on the second adhesive and thereafter performing a vacuum shaping process; and stacking a structural body on the third adhesive and thereafter hardening the members.