A hypergolic metal organic framework material for producing a hypergol when combined with an oxidizer, comprising a general structure M1-L-M2, wherein L is an aromatic organic linker comprising one or more unsaturated substituents, and wherein M1 and M2 are same or different metal cations.

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.1is 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.

An energetic composition and a method of unzipping polymer binders are disclosed, which includes localizing a heat feedback just near the reaction front by unzipping polymer binders employed to a nanothermite. The energetic composition includes an unzipping polymer binder employed to high load fuel and oxidizer particles.

An energetic composition and a method of unzipping polymer binders are disclosed, which includes localizing a heat feedback just near the reaction front by unzipping polymer binders employed to a nanothermite. The energetic composition includes an unzipping polymer binder employed to high load fuel and oxidizer particles.

A hypergolic co-crystal material for producing a hypergol when combined with an oxidizer; it has co-crystals composed at least of a hypergolic trigger component and an energetic coformer.

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 provides kits and compositions for e.g., hypergolic ignition of rocket propellant. The disclosed kits and the compositions comprise inter alia a fuel, a gelling agent, and an ignition agent; wherein the ignition agent is stably dissolved within the fuel.

The present invention provides kits and compositions for e.g., hypergolic ignition of rocket propellant. The disclosed kits and the compositions comprise inter alia a fuel, a gelling agent, and an ignition agent; wherein the ignition agent is stably dissolved within the fuel.

The present invention provides a particle and a composition for e.g., hypergolic ignition of rocket propellant. The disclosed particle and the composition comprise an energetic fuel additive and an ignition agent wherein the ignition agent is deposited on a surface of the particle.

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.