A gas generator is provided, the gas generator having a propellant cushion that prevents movement of propellant tablets or grains by providing a bias thereagainst. Furthermore, the cushion is formed from an auto-igniting material thereby functioning not only as a cushion, but also as an enhanced auto-ignition charge.

A method for recovering ammonium perchlorate from a solid composite propellant, the method being carried out at a temperature of less than 50 C. involving maceration of solid composite propellant fragments in the form of an aqueous suspension, the method being terminated when the ionic conductivity in the aqueous suspension reaches a stabilized value, of less than 60 mS/cm.

A method for recovering ammonium perchlorate from a solid composite propellant, the method being carried out at a temperature of less than 50 C. involving maceration of solid composite propellant fragments in the form of an aqueous suspension, the method being terminated when the ionic conductivity in the aqueous suspension reaches a stabilized value, of less than 60 mS/cm.

A tackifier is used resin in an energic material formulation comprising active materials and a polymeric binder to reduce or eliminate the use of a plasticiser in the formulation wherein the tackifier resin is compatible with the polymeric material.

A tackifier is used resin in an energic material formulation comprising active materials and a polymeric binder to reduce or eliminate the use of a plasticiser in the formulation wherein the tackifier resin is compatible with the polymeric material.

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.