Solid-fuel rocket propellants comprising an oxidizer, an oxophilic metal-halophilic metal formulation, and a binder are described herein. Further described are processes for preparing such propellants and methods of reducing hydrogen chloride production via the combustion of such propellants. Non-limiting examples of such formulations include aluminum-lithium alloys.

An improved armor piercing and pyrotechnic projectile for use in .50 military caliber rounds. Such projectiles contain a core, jacket, a base and a hollow nose housing pyrotechnic mixtures composed of sodium periodate and magnalium. The improved projectiles exhibit increased luminosity, and are non-toxic, safer, and environmentally benign compared to current state-of-the-art projectiles.

A propellant for a micro-gas generator, the propellant having 5-aminotetrazole, aluminum, a binder and an oxidizer and is substantially free from azodicarbonamide. This propellant substantially maintains its ballistic performance regardless of being aged at higher temperatures such as 120 C. Further, a method of manufacturing a propellant for a micro-gas generator, the method including providing a propellant mixture of 5-aminotetrazole, aluminum powder, potassium perchlorate, ethyl cellulose and fluoropolymers; adding acetone as a solvent to solvate ethyl cellulose and fluoropolymers; evaporating the acetone using a low level of vacuum until the mixture is a damp cake; and granulating and drying the damp cake forming dried propellant granules.

Compositions, devices, and methods for destroying chemical warfare agents, independent of their chemical make-up, include (i) at least one reactive metal; (ii) at least one oxidizer; and (iii) a binder. In one embodiment, the self-sustaining reactive composition includes magnesium powder, iron oxide powder, potassium perchlorate powder, and silicone gel. In another embodiment, the self-sustaining reactive composition includes manganese powder, lithium perchlorate powder, lithium peroxide powder, and silicone gel. The reactive metal(s), oxidizer(s), binder, and their respective amounts, are selected such that, following ignition of the composition, the composition is capable of producing a solid mass of ash (wicking composition) that increases the surface area of the chemical agent material and provides a site for combustion and/or thermal degradation of the chemical agent to occur.

Compositions, devices, and methods for destroying chemical warfare agents, independent of their chemical make-up, include (i) at least one reactive metal; (ii) at least one oxidizer; and (iii) a binder. In one embodiment, the self-sustaining reactive composition includes magnesium powder, iron oxide powder, potassium perchlorate powder, and silicone gel. In another embodiment, the self-sustaining reactive composition includes manganese powder, lithium perchlorate powder, lithium peroxide powder, and silicone gel. The reactive metal(s), oxidizer(s), binder, and their respective amounts, are selected such that, following ignition of the composition, the composition is capable of producing a solid mass of ash (wicking composition) that increases the surface area of the chemical agent material and provides a site for combustion and/or thermal degradation of the chemical agent to occur.

A composite propellant composition is disclosed that includes an oxidizer and fuel, wherein the oxidizer includes a trimodal mix of ammonium perchlorate containing three particle sizes present in substantially equal amounts, and wherein the fuel includes aluminum powder. Also disclosed are propellant grains and rocket motor assemblies that include the composite propellant composition, along with methods of making and using the compositions, grains, and assemblies.

A composite propellant composition is disclosed that includes an oxidizer and fuel, wherein the oxidizer includes a trimodal mix of ammonium perchlorate containing three particle sizes present in substantially equal amounts, and wherein the fuel includes aluminum powder. Also disclosed are propellant grains and rocket motor assemblies that include the composite propellant composition, along with methods of making and using the compositions, grains, and assemblies.