Abstract: Positive rocket motor pressure hull venting in the case of deck fires is vided by placement of thermite masses at spaced locations on the interior of the hull. Small cylindrical masses as well as strip formed masses are employed. The thermite mass includes a small amount of structurally formed aluminum as well as the conventional powdered aluminum.

Abstract: An improved rocket motor has a first layer of silicone rubber and a second ayer of an ablative lining placed between the rocket motor casing and the propellant grain. The ablative lining layer contains chopped novoloid fibers 14 microns in diameter and nominally 1 mm in length interspersed throughout a polymeric composition.

Abstract: A stress reducing liner for a solid rocket motor comprising a first layer polybutadiene based material, a second layer of perforated silicone rubber and a third layer of polybutadiene based material is fabricated by (1) coating the inner surface of a rocket motor casing with a curable polybutadiene based first layer material, (2) simultaneously heating and spinning the casing to cure the material in an even layer, (3) placing perforated silicone rubber over the cured first layer, (4) coating the silicone rubber layer with another uncured polybutadiene based material and (5) repeating the simultaneous heating and spinning procedure of step (2).

Abstract: Slurried rocket propellants and a spinning rocket motor wherein the propents have viscosities which enable them to form central cores when spun in spinning rocket motors, the motor having a diaphragm-like base plate which assists in transferring forward momentum through the propellant.

Abstract: In a method wherein propellant ingredients including a hydroxy terminated nder, an isocyanate curative therefor and transition metal compounds or traces thereof are mixed, worked into a suitable container and allowed to cure, gossypol is used to prolong the potlife of the propellant mix. Gossypol is dissolved in a portion of the hydroxy terminated binder material and the solution is utilized as a portion of the total binder. Final formulations containing from 0.02 to 0.1 weight percent gossypol are preferred although more gossypol may be used.