Abstract: 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.

Abstract: A solid rocket motor includes a combustion chamber bounded by an outer casing, a propellant grain within the combustion chamber, and an igniter within the outer casing for igniting the propellant grain. A nozzle is coupled to the combustion chamber for releasing hot gasses evolved from burning the propellant grain to provide thrust for propelling the solid rocket motor. The propellant grain is a self-extinguishing propellant grain that includes at least one fuel, at least one oxidizing agent, at least one binder, and at least one surfactant that imparts the self-extinguishing property. The propellant grain provides a burning rate as a function of pressure that includes a negative pressure dependence portion, wherein the burning rate in the negative pressure dependence portion decreases with increasing pressure until a cutoff pressure is reached which results in extinguishment of the propellant grain.

Abstract: Solid composite propellant compositions include at least one oxidizing agent, at least one binder, and at least one surfactant. The surfactant provides the solid propellant the property of being “self-extinguishing”, where the burning rate of the solid composite propellant as a function of pressure includes a negative pressure dependence portion, wherein the burning rate in the negative pressure dependence portion decreases with increasing pressure until a cutoff pressure is reached which results in extinguishment of the solid composite propellant. The solid composite propellant can also include at least one catalyst that modifies the burning rate of the solid composite propellant. Solid composite propellants can be extinguished without the need for depressurization by reaching a cutoff pressure, and with a tailored burning rate.

Abstract: Novel nano-sized rare earth metal oxide prepared from aqueous reverse micelles is provided. The engineered nanoparticles have large surface area to volume ratios, and sufficient oxygen vacancies on the surface of each particle, so that when mixed with carbon-containing combustible fuels, the particles remain suspended indefinitely; there is a significant reduction in soot and other by-products of combustion, an increase in engine efficiency and less fuel consumed per mile traveled in various vehicles, such as, but not limited to, automobiles, defense vehicles, airplanes, ships and other surface or air-bearing vehicles.

Abstract: Novel nano-sized rare earth metal oxide prepared from aqueous reverse micelles is provided. The engineered nanoparticles have large surface area to volume ratios, and sufficient oxygen vacancies on the surface of each particle, so that when mixed with carbon-containing combustible fuels, the particles remain suspended indefinitely; there is a significant reduction in soot and other by-products of combustion, an increase in engine efficiency and less fuel consumed per mile traveled in various vehicles, such as, but not limited to, automobiles, defense vehicles, airplanes, ships and other surface or air-bearing vehicles.