Embodiments of the present invention include a method for preparing and applying a slurry mixture to a bridge wire initiator which involves a slurry mixture that is relatively safer for a user to handle and in which the method is relatively less complex and shorter in duration for a user to prepare and apply the slurry mixture to the bridge wire initiator.

Electrically operated propellant thrust assist supplements an airplane's takeoff, landing or inflight maneuvers. Unlike conventional SRM propellants, the burn rate of the electrically operated propellant can be varied via an electrical input and even extinguished by interrupting the electrical to control a secondary thrust profile (e.g., amplitude, transition rates) to fulfill the needs of a given takeoff, inflight or landing maneuver and provide a smooth transition in and out of the maneuver. Multiple pairs of fixed thrusters (opposite sides of the fuselage), a single pair of gimbaled thrusters or a hybrid of fixed and gimbaled thrusters may be configured to provide all such maneuvers. Flight control inputs are passed back and forth through an interface to enable the thrust assist.

Electrically operated propellant thrust assist supplements an airplane's takeoff, landing or inflight maneuvers. Unlike conventional SRM propellants, the burn rate of the electrically operated propellant can be varied via an electrical input and even extinguished by interrupting the electrical to control a secondary thrust profile (e.g., amplitude, transition rates) to fulfill the needs of a given takeoff, inflight or landing maneuver and provide a smooth transition in and out of the maneuver. Multiple pairs of fixed thrusters (opposite sides of the fuselage), a single pair of gimbaled thrusters or a hybrid of fixed and gimbaled thrusters may be configured to provide all such maneuvers. Flight control inputs are passed back and forth through an interface to enable the thrust assist.

A downhole assembly comprises a first article; and a second article having a surface which accommodates a surface shape of the first article, wherein the first article is configured to provide a chemical, heat, or a combination thereof to facilitate the disintegration of the second article. A method comprises disposing a second article in a downhole environment; disposing a first article on the second article; the second article having a surface which accommodates a surface shape of the first article; performing a downhole operation; and disintegrating the first article to provide a chemical, heat, or a combination thereof that facilitates the disintegration of the second article.

A downhole assembly comprises a first article; and a second article having a surface which accommodates a surface shape of the first article, wherein the first article is configured to provide a chemical, heat, or a combination thereof to facilitate the disintegration of the second article. A method comprises disposing a second article in a downhole environment; disposing a first article on the second article; the second article having a surface which accommodates a surface shape of the first article; performing a downhole operation; and disintegrating the first article to provide a chemical, heat, or a combination thereof that facilitates the disintegration of the second article.

Embodiments directed to a method of manufacturing a pyrotechnic article for use with a thermal battery are disclosed. The method includes forming an iron oxide preform from iron oxide powder. The method also includes reducing the iron oxide preform to an iron preform made of metallic iron. The method further includes impregnating the iron preform with an oxidizer to form the pyrotechnic article.

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-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.

Energetic compositions and methods of forming components from the compositions are provided. In one embodiment, a composition includes aluminum, molybdenum trioxide, potassium perchlorate, and a binder. In one embodiment, the binder may include a silicone material. The materials may be mixed with a solvent, such as xylene, de-aired, shaped and cured to provide a self-supporting structure. In one embodiment, one or more reinforcement members may be added to provide additional strength to the structure. For example, a weave or mat of carbon fiber material may be added to the mixture prior to curing. In one embodiment, blade casting techniques may be used to form a structure. In another embodiment, a structure may be formed using 3-dimensional printing techniques.

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.