A high density, generally recognized as safe, hybrid rocket motor is described, having a density-specific impulse similar to a solid rocket motor, with good performance approaching or equal to a liquid rocket motor. These high density hybrid motors resolve the packaging efficiency/effectiveness problems limiting the application of safe, low cost hybrid motor technology.

A high density, generally recognized as safe, hybrid rocket motor is described, having a density-specific impulse similar to a solid rocket motor, with good performance approaching or equal to a liquid rocket motor. These high density hybrid motors resolve the packaging efficiency/effectiveness problems limiting the application of safe, low cost hybrid motor technology.

Energetic compounds based on bismuth salts with reduced toxicity that are obtained through the reaction of soluble bismuth salts with soluble salts of organic or inorganic energetic compounds based on azides, derivatives aromatic nitro compounds or nitrogenous heterocyclic compounds, together with the methods for their preparation and application.

Energetic compounds based on bismuth salts with reduced toxicity that are obtained through the reaction of soluble bismuth salts with soluble salts of organic or inorganic energetic compounds based on azides, derivatives aromatic nitro compounds or nitrogenous heterocyclic compounds, together with the methods for their preparation and application.

Exemplary embodiments of an ignition apparatus are disclosed herein. Each ignition apparatus is configured for use in a projectile, such as an artillery projectile, rocket, missile, drone, and other similar projectiles. In each exemplary embodiment disclosed herein, the ignition apparatus initiates an ignition sequence that is the reverse of the ignition sequences implemented by conventional ignition devices that utilize pre-loaded or pre-compressed spring-operated firing pins. Each exemplary embodiment of the ignition apparatus disclosed herein utilizes the extreme axial acceleration of the projectile to arm and initiate the ignition sequence.

A high density, generally recognized as safe hybrid rocket motor is described which has a density-specific impulse similar to a solid rocket motor, with good performance approaching or equal to a liquid rocket motor. These high density hybrid motors resolve the packaging efficiency/effectiveness problems limiting the application of safe, low cost hybrid motor technology.

A high density, generally recognized as safe hybrid rocket motor is described which has a density-specific impulse similar to a solid rocket motor, with good performance approaching or equal to a liquid rocket motor. These high density hybrid motors resolve the packaging efficiency/effectiveness problems limiting the application of safe, low cost hybrid motor technology.

The invention relates to a pyrotechnic agent containing at least one azotetrazolate as a component thereof.

The invention relates to a pyrotechnic agent containing at least one azotetrazolate as a component thereof.

An igniter composition has (i) a source of copper selected from basic copper nitrate, copper oxide, copper hydroxide, and/or copper complex of guanylurea nitrate, (ii) one or more oxidizers, (iii) a binder selected from guanidine nitrate and/or guanylurea nitrate, and (iv) an inorganic fuel comprising an elemental metal or metal hydride selected from the group consisting of: titanium, silicon, aluminum, magnesium, iron, and combinations thereof. The igniter composition may be substantially free of boron or contain minimal amounts of boron. A minimum flame temperature at combustion (T.sub.c) of about 2300K (2,027 C.). Such a mixture may be spray dried to form a powder that is compacted to form a solid igniter composition, such as a pellet or grain. The mixture that is spray dried may have a heat of explosion (HEX) of about 1,000 calories per gram (cal/g). Inorganic fuel can then be added to the spray-dried powder.