A concealed amalgamated neutralizer covertly combines neutralizer material comprised of various combinations of inert materials such as calcium carbonate or silicates with common explosive material for the prevention of malicious use of the explosive material in improvised explosive devices. The concealed amalgamated neutralizer device may vary in shape, size, and color and is therefore adaptable to varying methods of containment typified by common pyrotechnic products. The neutralizer material mimics the explosive material of the pyrotechnic products without detection. Upon disassembly of a concealed amalgamated neutralizer device, the neutralizer material is mixed with and neutralizes the explosive material rendering the explosive material useless as a component for an improvised explosive device.

A concealed amalgamated neutralizer covertly combines neutralizer material comprised of various combinations of inert materials such as calcium carbonate or silicates with common explosive material for the prevention of malicious use of the explosive material in improvised explosive devices. The concealed amalgamated neutralizer device may vary in shape, size, and color and is therefore adaptable to varying methods of containment typified by common pyrotechnic products. The neutralizer material mimics the explosive material of the pyrotechnic products without detection. Upon disassembly of a concealed amalgamated neutralizer device, the neutralizer material is mixed with and neutralizes the explosive material rendering the explosive material useless as a component for an improvised explosive device.

A hybrid rocket solid fuel grain having a cylindrical shape and defining a center port is additive manufactured from a compound of thermoplastic fuel and passivated nanocomposite aluminum additive. The fuel grain comprises a stack of fused layers, each formed as a plurality of fused abutting concentric circular beaded structures of different radii arrayed defining a center port. During operation, an oxidizer is introduced along the center port, with combustion occurring along the exposed port wall. Each circular beaded structure possesses geometry that increases the surface area available for combustion. As each layer ablates the next abutting layer, exhibiting a similar geometry is revealed, undergoes a gas phase change, and ablates. This process repeats and persists until oxidizer flow is terminated or the fuel grain material is exhausted. To safety achieve this construction, a fused deposition additive manufacturing apparatus, modified to shield the nanocomposite material from the atmosphere is used.

A propellant load includes a propellant block, containing energetic charges in a crosslinked binder, arranged in a structure having a thermal protection; the crosslinked binder being an energetic binder including a polymer, more polar than hydroxytelechelic polybutadiene (HTPB), which is crosslinked and an energetic plasticizer, the polymer non-crosslinked representing less than 14% of the volume of the propellant block; a bonding layer, based on crosslinked hydroxytelechelic polybutadiene (HTPB), between the thermal protection and the propellant block; and a system for mechanical reinforcement of the bonding layer/propellant block bond, present on at least part of the bonding layer/propellant block interface, including grains embedded in part in the bonding layer and the complementary part thereof being embedded in the propellant block: made of a pyrotechnically inert material, and that has a surface energy greater than 34 mJ/m.sup.2; and the largest dimension of which is between 0.3 and 5.2 mm.

A propellant load includes a propellant block, containing energetic charges in a crosslinked binder, arranged in a structure having a thermal protection; the crosslinked binder being an energetic binder including a polymer, more polar than hydroxytelechelic polybutadiene (HTPB), which is crosslinked and an energetic plasticizer, the polymer non-crosslinked representing less than 14% of the volume of the propellant block; a bonding layer, based on crosslinked hydroxytelechelic polybutadiene (HTPB), between the thermal protection and the propellant block; and a system for mechanical reinforcement of the bonding layer/propellant block bond, present on at least part of the bonding layer/propellant block interface, including grains embedded in part in the bonding layer and the complementary part thereof being embedded in the propellant block: made of a pyrotechnically inert material, and that has a surface energy greater than 34 mJ/m.sup.2; and the largest dimension of which is between 0.3 and 5.2 mm.

The invention relates to a pyrotechnic gas generator component including an inlet stage formed by a pyrotechnic detonator composition and an intermediate stage disposed between the inlet stage and an outlet stage formed by at least one gas generator composition, said intermediate stage being formed by a compressed black powder layer.

The invention is directed to a propellant charge for guns, to a combination of a propellant charge and a primer, to a firearms cartridge, and to a method for modifying the surface of a propellant charge.

The propellant charge of the invention comprises multiple propellant grains, wherein an exterior part of part of the propellant grains has been subjected to a surface modification treatment comprising the successive steps of suspending propellant grains in water to prepare a slurry, adding an organic solvent to the propellant grains before, after and/or during the preparation of the slurry, mixing the slurry that comprises water and organic solvent for a period of 120 minutes or less, lowering the concentration of organic solvent, removing organic solvent, and drying the propellant grains to remove water;
wherein part of the propellant grains has not been subjected to the surface modification treatment.

The invention is directed to a propellant charge for guns, to a combination of a propellant charge and a primer, to a firearms cartridge, and to a method for modifying the surface of a propellant charge.

The propellant charge of the invention comprises multiple propellant grains, wherein an exterior part of part of the propellant grains has been subjected to a surface modification treatment comprising the successive steps of suspending propellant grains in water to prepare a slurry, adding an organic solvent to the propellant grains before, after and/or during the preparation of the slurry, mixing the slurry that comprises water and organic solvent for a period of 120 minutes or less, lowering the concentration of organic solvent, removing organic solvent, and drying the propellant grains to remove water;
wherein part of the propellant grains has not been subjected to the surface modification treatment.

A fuel grain assembly for a hybrid rocket engine includes a hybrid fuel grain including fuel grain material, wherein an outermost portion of the fuel grain material defines an outer surface of the fuel grain, and wherein the fuel grain material includes a polymer based rocket fuel material; and a solid propellant material disposed in contact with the fuel grain material of the hybrid fuel grain, wherein the solid propellant material includes an oxidizer and a binder material, wherein a hollow combustion port extends through the fuel grain assembly, wherein at least a portion of a wall of the hollow combustion port is defined by the solid propellant material.

A fuel grain assembly for a hybrid rocket engine includes a hybrid fuel grain including fuel grain material, wherein an outermost portion of the fuel grain material defines an outer surface of the fuel grain, and wherein the fuel grain material includes a polymer based rocket fuel material; and a solid propellant material disposed in contact with the fuel grain material of the hybrid fuel grain, wherein the solid propellant material includes an oxidizer and a binder material, wherein a hollow combustion port extends through the fuel grain assembly, wherein at least a portion of a wall of the hollow combustion port is defined by the solid propellant material.