Patent ID: 7578452

Claim:
An ablative rocket exhaust assembly for deployment on a rocket, the ablative rocket exhaust assembly comprising: a first ablative composite sub-assembly and a second ablative composite sub-assembly; a plurality of radial openings formed through an outer wall of said first ablative composite sub-assembly, each radial opening in said plurality of radial openings extending in radial direction substantially perpendicular to the longitudinal axis of the ablative rocket nozzle; a first plurality of axial openings in said first ablative composite sub-assembly; a second plurality of axial openings in said second ablative composite sub-assembly and generally aligning with said first plurality of axial openings; and a film adhesive disposed between said first ablative composite sub-assembly and said second ablative composite sub-assembly, said film adhesive including a third plurality of openings therethrough generally aligning with said first plurality of axial openings and said second plurality of axial openings, said film adhesive joining together said first ablative composite sub-assembly to said second ablative composite sub-assembly when said film adhesive is cured.