Provided is a high pressure polymorph of croconic acid. The high pressure polymorph of croconic acid has an unexpectedly high energy release and is suitable for use in detonable compositions. The high pressure polymorph of croconic acid is recoverable to ambient conditions and exhibits only a modest increase in density but a greatly improved energy release.

Embodiments disclosed herein provide an Explosive Device Simulator (EDS). Embodiments of the Explosive Device Simulator may include two or more chemical components that are non-explosive when separated from each other within the EDS, but which form an explosive mixture or substance when combined. Because the individual chemical components are non-explosive, the Explosive Device Simulator may be stored, transported and handled safely for long periods of time and without increased security, protective measures, or special training. Further, the chemical components may be chosen such that the Explosive Device Simulator creates a realistic explosion (e.g. loud and bright), but which produces minimal concussive forces and is therefore safer to use as a training aid.

Embodiments disclosed herein provide an Explosive Device Simulator (EDS). Embodiments of the Explosive Device Simulator may include two or more chemical components that are non-explosive when separated from each other within the EDS, but which form an explosive mixture or substance when combined. Because the individual chemical components are non-explosive, the Explosive Device Simulator may be stored, transported and handled safely for long periods of time and without increased security, protective measures, or special training. Further, the chemical components may be chosen such that the Explosive Device Simulator creates a realistic explosion (e.g. loud and bright), but which produces minimal concussive forces and is therefore safer to use as a training aid.

A method for the manufacture of a composite fragmenting material having exothermic properties includes the steps of packing a mold with preformed metal fragments; filling interstitial spaces surrounding the metal fragments with a reactive metal powder to form a mixture; and then sintering the mixture at a temperature effective to both coat the metal fragments with the reactive metal powder and to bond the metal fragments together. In one embodiment the composite fragmenting material is formed into a nosecone for a warhead.

A method for the manufacture of a composite fragmenting material having exothermic properties includes the steps of packing a mold with preformed metal fragments; filling interstitial spaces surrounding the metal fragments with a reactive metal powder to form a mixture; and then sintering the mixture at a temperature effective to both coat the metal fragments with the reactive metal powder and to bond the metal fragments together. In one embodiment the composite fragmenting material is formed into a nosecone for a warhead.

The present invention provides a Fischer-Tropsch gasoil fraction having: (a) an initial boiling point of at least 220 C.; (b) a final boiling point of at most 360 C.; (c) a kinematic viscosity at 25 C. according to ASTM D445 of from 3.8 to 4.4 cSt; and (d) of a flash point according to ASTM D93 of at least 100 C. In another aspect the present invention provides a composition and the use of a Fischer-Tropsch gasoil fraction according to the invention.

The present invention provides a Fischer-Tropsch gasoil fraction having: (a) an initial boiling point of at least 220 C.; (b) a final boiling point of at most 360 C.; (c) a kinematic viscosity at 25 C. according to ASTM D445 of from 3.8 to 4.4 cSt; and (d) of a flash point according to ASTM D93 of at least 100 C. In another aspect the present invention provides a composition and the use of a Fischer-Tropsch gasoil fraction according to the invention.

A rocket propellant includes a hydrocarbon blend having a total aromatic compounds content less than 0.5 mass percent, a specific energy of at least 18.4 KBtu/lb, and a mass density of at least 0.8150 grams per cubic centimeter. The propellant, which can be prepared by blending a refined kerosene with an isoparaffin and/or a cycloparaffin, exhibits a high volumetric heat of combustion and excellent thermal stability. This combination of properties is especially useful for fueling reusable launch vehicles employing regenerative cooling of engine components.

A rocket propellant includes a hydrocarbon blend having a total aromatic compounds content less than 0.5 mass percent, a specific energy of at least 18.4 KBtu/lb, and a mass density of at least 0.8150 grams per cubic centimeter. The propellant, which can be prepared by blending a refined kerosene with an isoparaffin and/or a cycloparaffin, exhibits a high volumetric heat of combustion and excellent thermal stability. This combination of properties is especially useful for fueling reusable launch vehicles employing regenerative cooling of engine components.

A combustion system includes a reactant storage device configured to store lithium; a combustion device configured to receive the lithium from the reactant storage device and react the lithium with an oxidizer to generate heat energy; a product storage device configured to store reaction products resulting from the reaction of the lithium and the oxidizer; and a recovery device configured to recover lithium from the reaction products and provide the lithium to the storage device.