Abstract: A flame inhibitor coating for application to those surfaces of a solid prllant grain in a rocket motor where burning is not desired such as the aft end of a perforated propellant grain which includes a barrier layer of a mixture of amine silane, a trialkoxypropylsilylamino prepolymer, and diglycidylether of polypropylene glycol, an epoxy applied to the grain surface and allowed to cure to a polysiloxane layer, and a flame inhibitor layer applied over the barrier layer consisting of a mixture of hydroxyl terminated polybutadiene and dimeryl diisocyanate with flake aluminum which is applied over the barrier layer and allowed to cure. The barrier layer prevents migration of nitrate esters from the solid propellant grain to the flame inhibitor layer thus preventing peeling and reduction of flame inhibiting properties. The polysiloxane barrier layer is also useful in itself as a flame inhibitor and can also be employed between the insulator/liner of the rocket motor and the solid propellant grain.

Abstract: Energetic materials exhibiting low sensitivity comprise a solid solution of nitroaliphatic oxidizer, preferably trinitroethyl derivatives, in plasticized thermoplastic elastomer such as a block copolymer of polystyrene and polyacrylate plasticized with dioctyl adipate. The energetic material is prepared by forming molten plasticized elastomer and then incrementally dissolving the oxidizer in the molten binder.

Abstract: A gas generating composition containing glycidyl azide polymer and a high trogen content additive selected from the group consisting of guanylaminotetrazole nitrate, bis(triaminoguanidinium)5,5'azotetrazole, ammonium 5-nitraminotetrazole and high bulk density nitro guanidine generates large quantities of nitrogen gas upon burning and can be used to extinguish fires.

Abstract: The present invention relates to a method for preparing an in situ cured ster explosive by mixing explosive crystals with a prepolymer solution comprising a carboxyl (or hydroxyl)-terminated hydrophobic polyester and epoxidized linseed oil with chromium octanoate as a catalyst. The explosive mixture is pressed into desired size and cured at 60.degree. C. to 70.degree. C. for about 96 hours. The resulting in situ cured explosive has desirable safety and physical properties.

Abstract: A multiple component catalyst system for curing of energetic urethane bins for solid fuel propellants and gas generators based upon curing of glycidyl-azide polymer and isocynate curative mixtures. Void or bubble free propellant grains are obtained by employing a cure catalyst composed of a mixture of triphenyl bismuth and dibutyltin dilaurate, preferably in a respective ratio of about 10:1 by weight. The void free propellant grains have burn characteristics acceptable for missile propulsion applications.