The present invention relates to a hypergolic two-component system for rocket engines, including a fuel and an oxidising agent provided in a manner separated from one another and can be reacted in a rocket engine by bringing them into contact with one another. The fuel is an ionic liquid comprising a thiocyanate anion and one or more cations. The cation or cations are selected from one or more imidazolium ions of the general formula I, triazolium ions of the general formula II or III, and/or tetrazolium ions of the general formula IV, where R.sub.1 is a C.sub.1- to C.sub.6-alkyl radical or a C.sub.2- to C.sub.6-alkenyl radical, where R.sub.2 is hydrogen or a C.sub.1- to C.sub.6-alkyl radical or a C.sub.2- to C.sub.6-alkenyl radical, and where X.sub.1, X.sub.2 and X.sub.3 are each independently hydrogen, a C.sub.1- to C.sub.6-alkyl radical or a C.sub.2- to C.sub.6-alkenyl radical, and the oxidising agent comprises hydrogen peroxide.

The present invention relates to a hypergolic two-component system for rocket engines, including a fuel and an oxidising agent provided in a manner separated from one another and can be reacted in a rocket engine by bringing them into contact with one another. The fuel is an ionic liquid comprising a thiocyanate anion and one or more cations. The cation or cations are selected from one or more imidazolium ions of the general formula I, triazolium ions of the general formula II or III, and/or tetrazolium ions of the general formula IV, where R.sub.1 is a C.sub.1- to C.sub.6-alkyl radical or a C.sub.2- to C.sub.6-alkenyl radical, where R.sub.2 is hydrogen or a C.sub.1- to C.sub.6-alkyl radical or a C.sub.2- to C.sub.6-alkenyl radical, and where X.sub.1, X.sub.2 and X.sub.3 are each independently hydrogen, a C.sub.1- to C.sub.6-alkyl radical or a C.sub.2- to C.sub.6-alkenyl radical, and the oxidising agent comprises hydrogen peroxide.

Provided is an emulsion explosive composition having voids/bubbles formed from one or more noble gases dispersed therein. Also provided is a method of manufacturing an emulsion explosive composition that includes mechanically and/or pneumatically infusing an emulsion explosive composition with a noble gas so as to create voids/bubbles formed from one or more noble gases. The noble gases can be contained within closed-cell micro-spheres that are dispersed throughout the emulsion explosive composition.

A combustion tool fuel cell is provided having enhanced low temperature operation, including a fuel composition comprising at least one hydrocarbon component with a total vapor pressure equal or above 95 psig at 21 C.

A combustion tool fuel cell is provided having enhanced low temperature operation, including a fuel composition comprising at least one hydrocarbon component with a total vapor pressure equal or above 95 psig at 21 C.

The present disclosure provides a fire starter that does not require oxygen from the air to ignite or maintain a flame and makes it easy to ignite using one or no fingers, such as teeth. A fire starter includes a burnable casing forming a sealed chamber. A first burnable mixture and a second burnable mixture are separately disposed in the sealed chamber. The first burnable mixture can form a flame without oxygen from the air. An igniter is disposed in the sealed chamber adjacent to the first burnable mixture and configured to generate a first thermal event to ignite the first burnable mixture without oxygen from the air. The first burnable mixture combusts during the first thermal event and triggers a second thermal event to ignite the second burnable mixture. An actuator is configured to activate the igniter to generate the first thermal event without using more than one finger.

The present disclosure provides a fire starter that does not require oxygen from the air to ignite or maintain a flame and makes it easy to ignite using one or no fingers, such as teeth. A fire starter includes a burnable casing forming a sealed chamber. A first burnable mixture and a second burnable mixture are separately disposed in the sealed chamber. The first burnable mixture can form a flame without oxygen from the air. An igniter is disposed in the sealed chamber adjacent to the first burnable mixture and configured to generate a first thermal event to ignite the first burnable mixture without oxygen from the air. The first burnable mixture combusts during the first thermal event and triggers a second thermal event to ignite the second burnable mixture. An actuator is configured to activate the igniter to generate the first thermal event without using more than one finger.

A catalyst for decomposing high-concentration hydrogen peroxide comprises an active layer on a carrier comprising gamma-phase alumina. The carrier can also comprise aluminum, with the gamma-phase alumina forming a passivating layer on the surface of the aluminum. The active layer can comprise platinum. Apparatus for decomposing hydrogen peroxide can include the catalyst in a decomposition chamber arranged to receive hydrogen peroxide. The apparatus can be used as a thruster, comprising a nozzle arranged to generate thrust by directing exhaust gases in a specific direction. For example, the thruster can be a monopropellant, bipropellant, or hybrid thruster. In other embodiments, the apparatus can be used as a gas generator or a fuel cell.

The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit maneuvers and maintenance, attitude control and deorbiting of spacecraft, and/or 2) propellant settling, attitude and roll control of missiles, launchers and space planes. The present invention also relates to a dual mode chemical rocket engine for use in such systems. The engine uses low-hazardous storable liquid propellants and can be operated either in monopropellant mode or in bipropellant mode. The monopropellants used are a low-hazard liquid fuel-rich monopropellant, and a low-hazard liquid oxidizer-rich monopropellant, respectively.

The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit maneuvers and maintenance, attitude control and deorbiting of spacecraft, and/or 2) propellant settling, attitude and roll control of missiles, launchers and space planes. The present invention also relates to a dual mode chemical rocket engine for use in such systems. The engine uses low-hazardous storable liquid propellants and can be operated either in monopropellant mode or in bipropellant mode. The monopropellants used are a low-hazard liquid fuel-rich monopropellant, and a low-hazard liquid oxidizer-rich monopropellant, respectively.