초록

A nozzle assembly capable of controlling the hot exhaust gases which flow from the burning solid rocket propellant.

대표청구항 ▼

A rocket nozzle assembly having: an insulated shell comprised of a stationary shell and shell insulation adjacent thereto; a flexible seal configuration comprised of a core and adjacent thermal barrier encompassed in part by a forward end ring, an aft end ring and an insulator tip, said core and the

A rocket nozzle assembly having: an insulated shell comprised of a stationary shell and shell insulation adjacent thereto; a flexible seal configuration comprised of a core and adjacent thermal barrier encompassed in part by a forward end ring, an aft end ring and an insulator tip, said core and thermal barrier having a first and a second external side having ozone barriers adjacent thereto; a plurality of bolts circumferentially positioned, affixing said stationary shell and said aft end ring; an exit cone assembly comprised of an exit cone liner having two ends, affixed to an exit cone adapter at one end and a compliance ring at the opposite end, said liner being overwrapped with an exit cone structure, and said structure and said compliance ring being covered in part with insulation; a plurality of bolts circumferentially positioned, affixing said forward end ring and said adapter; a throat assembly comprising an integral throat entrance and throat insulation adjacent thereto, said throat insulation bonded to said forward end ring, said adapter and said liner; and an entrance cap attached to said throat assembly and said forward end ring.