Abstract: A non-radiating cloth exit cone for a rocket nozzle includes a flared woven refractory cloth structure having the shape of the frustum of a cone with a refractory felt sewn to the exterior surface of the cloth structure for thermal insulation of the cloth structure and a sacrificial ablative material comprising tufts of refractory material incorporated in the interior surface of the cloth structure, the cloth structure providing the primary supporting structure for transmitting the rocket motor thrust forces to the rocket nozzle.

Abstract: 1. An igniter adapted to be positioned in the convergent portion of the nozzle of a rocket engine, said igniter comprising, a tapered combustible plastic casing having a small end and a large end, said casing having a stepped recess therein comprising a large cavity formed in the large end of said casing and a relatively small cavity opening into the inner end of said large cavity, a squib including a primer charge positioned in said small cavity, a body of pyrotechnic material positioned in said large cavity adjacent to said primer charge, a closure disc positioned in said large cavity to hold said pyrotechnic material therein, and squib-activating means for igniting said primer charge, said activating means extending from said squib through said casing and out the small end thereof, the inner end of said small cavity and the small end of said casing being substantially spaced from one another to provide a substantial body of combustible plastic therebetween.