Patent ID: 6330792
Filing Date: 2001-12-18
Classification: B29C,B29L,F02K,Y10S

Abstract:
A method for making in substantially one piece a thrust chamber assembly for a rocket engine, said assembly having a combustion chamber a throat and a nozzle connected in series, comprisinga. providing a two-piece mandrel having a configuration of said combustion chamber, throat and nozzle portions portion, said mandrel having an axis;b. wrapping the mandrel with a generally flat fabric tape saturated with a curable thermosetting resin; said tape having first and second edges, said tape width being positioned at an acute angle with respect to said axis such that one of the edges of the tape is in contact with the mandrel and the other edge is spaced from the mandrel;c. curing the thermosetting resin;d. wrapping the assembly with a tow of graphite fibers wetted with an epoxy resin to form a structural layer; ande. curing the epoxy resin.