The present invention is directed to a process for preparing light curable energetic polymeric binders. The process for preparing such binder comprises the steps of mixing a pre-polymer such as PGN or GAP having a terminal hydroxyl group with a solvent and adding reactants wherein the reactant has a light curable moiety and a pre-polymer reactive moiety. Catalysts such as carbodiimide and DMAP may be further added to the mixture.

An explosive with reduced detonation performance that includes an explosive powder that detonates with a reaction velocity of less than 5000 feet per second, a polymer resin, and an inert filler.

An explosive with reduced detonation performance that includes an explosive powder that detonates with a reaction velocity of less than 5000 feet per second, a polymer resin, and an inert filler.

An igniter tube consisting of a combustible tube, on the inner face of which an ignition charge is deposited along the length of said combustible tube. The invention also relates to a method for producing the igniter tube.

An igniter tube consisting of a combustible tube, on the inner face of which an ignition charge is deposited along the length of said combustible tube. The invention also relates to a method for producing the igniter tube.

The present invention is a composite solid propellant designed to operate in three distinct combustion regimes under various pressure states in the combustion chamber of a solid rocket motor. The design of this propellant facilitates desirable rocket motor operational characteristics, including throttleability, extinguishment, and self-destruction or detonability. The propellant contains ingredients that modify the propellant combustion characteristics to provide the desired behavior, including a surfactant and unaggregated, unagglomerated dispersed primary nanoparticles of aluminum in a polymer binder.

The present invention is a composite solid propellant designed to operate in three distinct combustion regimes under various pressure states in the combustion chamber of a solid rocket motor. The design of this propellant facilitates desirable rocket motor operational characteristics, including throttleability, extinguishment, and self-destruction or detonability. The propellant contains ingredients that modify the propellant combustion characteristics to provide the desired behavior, including a surfactant and unaggregated, unagglomerated dispersed primary nanoparticles of aluminum in a polymer binder.

A method of making a polysilylether (PSE) polymer includes: cooling a solution of diethylamine to 0° C. under argon; adding cold dialkyldichlorosilane to form a first mixture; slowly warming the first mixture to form dialkylbis(diethylamino)silane; diluting the first mixture with hexane then filtering via cannula; evaporating the hexane and excess diethylamine; purifying the dialkylbis(diethylamino)silane under vacuum distillation; adding the dialkylbis(diethylamino)silane to a solution of diol dissolved in tetrahydrofuran to form a second mixture; heating the second mixture to 60° C. while reflux condensing, and cooling and concentrating the second mixture under vacuum to form a resultant mixture containing the polysilylether (PSE) polymer.

The invention is directed to a solid, porous material for generating hydrogen gas, said material having a porosity of 20 to 75 vol %, and a composition comprising, based on the weight of the material, 50 to 99% of a boron hydride compound, and 1 to 30% of a binder. A further aspect of the invention relates to a gas generator comprising said material and use thereof in aerospace applications.

A method of making a fuel grain for a hybrid rocket engine includes deposing beads of fuel grain material onto mandrel using additive manufacturing to form a cylindrical fuel grain, each bead including a polymer based rocket fuel material and a nanoscale metallic material. The deposing includes deposing multiple, adjacent beads to form concentric layers of beads, wherein a composition of the beads of the fuel grain material differs between the beads of a first layer and the beads of a second layer of the fuel grain.