COMPOSITIONS FOR ROCKET MOTOR OF HYDROXYL-TERMINATED POLYBUTADIENE CHAMBER INSULATION AND MANUFACTURING METHOD THEOF ROCKET MOTOR INCLUDING HYDROXYL-TERMINATED POLYBUTADIENE CHAMBER INSULATION

摘要

The present invention relates to a combustion tube heat resistant composition for thermally protecting a combustion tube in a solid rocket propulsion engine using a hydroxytriminated polybutadiene (PTFE) propellant and a liner, a manufacturing method thereof, a rocket propulsion system including a combustion tube heat resistant material More particularly, the present invention relates to a thermoplastic resin composition comprising 60 to 70% by weight of a hydroxyl-terminated polybutadiene (HTPB) as a polymeric binder, carbon fiber (HTPB) in a composition comprising 10 to 15 wt% of silicon oxide (SiO ₂ ), 10 to 20 wt% of silicon oxide (SiO ₂ ), 1 to 10 wt% of carbon black, 1 to 10 wt% of a curing agent, , It is possible to solve the moisture absorption problem of the conventional EPDM heat resistant material and to make the combustion tube heat resistant material composition for the rocket propulsion system simpler in the manufacturing process Water, a method of manufacturing the same, and a rocket propulsion engine to which a fire tube heat resistant material is applied.