causing the fibers to be necked down and pressed onto the outer configuration of the nozzle insert when linear layer 38 has been made to conform to the outer configuration of nozzle insert 28 as illustrated in fig4 the space between radial layers 40 and 42 is filled in by radially wrapping this area with fibers 22 to fill in as illustrated at 44 and provide the desired structure and strength of the structure if desired additional radial plies can be wrapped on the rocket motor structure as desired to provide the radial strength needed for the rocket motor case and integral nozzle structure once winding of the rocket motor case and integral nozzle is complete the strands are cut at groove 32 to define the distal end of the rocket motor case mandrel 12 with the rocket motor case wound thereon is then removed from the winding machine and placed in an oven for curing the fibers with the epoxy resin that was placed on fibers 22 as they were being wound into the rocket motor and integral nozzle structure after curing of the rocket motor and integral nozzle in a conventional manner the cured rocket motor and integral nozzle structure are removed from mandrel sections 24 and 26 in a conventional manner if desired the outer surface of cured rocket motor and integral nozzle structure can be machined to provide a smooth shape of the outer surface desired.