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.

Solid propellant systems include a main propellant and a secondary propellant in contact with the first propellant that exhibits autoignition temperatures of at least about 100° F. lower than the autoignition temperature of the main propellant. The secondary propellant of the present invention is most advantageously employed with conventional AP-containing solid propellant formulations as the main propellant, especially formulations containing both AP, an energetic solid, and a binder. In especially preferred forms, the secondary propellant will include a nitramine which is at least one selected from nitroguanidine (NQ), cyclotrimethylene trinitramine (RDX) and cyclotetramethylenetetranitramine (HMX), and a binder which is at least one selected from HTPB, HTPE or glycidyl azide polymer (GAP). Most preferably, the secondary propellant will include a combination of nitramines which includes NQ and one of RDX or HMX.

Solid propellant systems include a main propellant and a secondary propellant in contact with the first propellant that exhibits autoignition temperatures of at least about 100° F. lower than the autoignition temperature of the main propellant. The secondary propellant of the present invention is most advantageously employed with conventional AP-containing solid propellant formulations as the main propellant, especially formulations containing both AP, an energetic solid, and a binder. In especially preferred forms, the secondary propellant will include a nitramine which is at least one selected from nitroguanidine (NQ), cyclotrimethylene trinitramine (RDX) and cyclotetramethylenetetranitramine (HMX), and a binder which is at least one selected from HTPB, HTPE or glycidyl azide polymer (GAP). Most preferably, the secondary propellant will include a combination of nitramines which includes NQ and one of RDX or HMX.

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.

Solid propellant systems include a main propellant and a secondary propellant in contact with the first propellant that exhibits autoignition temperatures of at least about 100° F. lower than the autoignition temperature of the main propellant. The secondary propellant of the present invention is most advantageously employed with conventional AP-containing solid propellant formulations as the main propellant, especially formulations containing both AP, an energetic solid, and a binder. In especially preferred forms, the secondary propellant will include a nitramine which is at least one selected from nitroguanidine (NQ), cyclotrimethylene trinitramine (RDX) and cyclotetramethylenetetranitramine (HMX), and a binder which is at least one selected from HTPB, HTPE or glycidyl azide polymer (GAP). Most preferably, the secondary propellant will include a combination of nitramines which includes NQ and one of RDX or HMX.

A precursor formulation comprising, before curing, a hydroxyl-terminated polybutadiene (HTPB) prepolymer or a hydroxyl-terminated polyether (HTPE) prepolymer, an oxidizer, a dimer fatty diol, and an isocyanate curative. A solid propellant comprising a reaction product of the HTPB prepolymer or HTPE prepolymer, the dimer fatty diol, and the isocyanate curative is also disclosed, as is a rocket motor comprising a case and a solid propellant in the case, the solid propellant comprising the reaction product and an oxidizer. A method of reducing a burn rate of a solid propellant is also disclosed.

A precursor formulation comprising, before curing, a hydroxyl-terminated polybutadiene (HTPB) prepolymer or a hydroxyl-terminated polyether (HTPE) prepolymer, an oxidizer, a dimer fatty diol, and an isocyanate curative. A solid propellant comprising a reaction product of the HTPB prepolymer or HTPE prepolymer, the dimer fatty diol, and the isocyanate curative is also disclosed, as is a rocket motor comprising a case and a solid propellant in the case, the solid propellant comprising the reaction product and an oxidizer. A method of reducing a burn rate of a solid propellant is also disclosed.

Provided are a gas generant composition, a preparation method, and a gas generator containing the composition. The gas generant composition includes components having the following contents, in percent by mass: 40% to 60% of guanidine nitrate, 25% to 50% of basic copper nitrate, 0% to 7% of ammonium perchlorate, 1% to 10% of a slag-forming agent, and 0.05% to 5% of a release agent/lubricant, the slag-forming agent is used as a form-retaining agent, so that the tablets can retain their form before combustion very well after combustion, thereby completely avoiding burning of an inflatable bag due to melting and splashing of the combusted tablets. Moreover, ammonium perchlorate is used as auxiliary oxidizers, thereby reducing the amount of basic cupric nitrate used and reducing molten copper residues. The gas generant composition is mainly used in a gas generator for vehicle airbag.

The present invention comprises formulations and method for additive manufacturing comprising: a pot-stable photo-curable polymer; one or more fillers; and one or more additives, wherein the formulation cures into a polymer in six hours or less upon exposure to light. In certain examples, the additive manufacturing is a moldless method of additive manufacturing by preparing a formulation comprising: a pot-stable photo-curable polymer, one or more fillers, and one or more additives, and exposing the formulation to light in an amount that substantially cures the polymer in 6 hours or less.