Abstract: The present invention relates to suspensions of hexanitrohexaazaisowurtzitane crystals in a liquid phase (said liquid phase is composed, to at least 85% by weight, of a nonsolvent for hexanitrohexaazaisowurtzitane, said nonsolvent consisting of at least one nonflammable hydrofluoroether, and includes from 0 to less than 15% by weight of an organic solvent for hexanitrohexaazaisowurtzitane, more volatile than said nonsolvent, chosen from the group consisting of esters, nitriles, ketones and their mixtures), the production of said suspensions and their use to manufacture pyrotechnic objects. The use of said at least one hydrofluoroether as nonsolvent is particularly appropriate.

Abstract: A subject matter of the present invention is: the compounds of formula (I): in which: and Het is an azolyl radical: nitroazolyl or tetrazolyl; with the exception of 3-nitro-4-(4-nitro-1,2,3-triazol-1-yl)furazan; the preparation of said compounds; and the energetic compositions including at least one compound chosen from said compounds of formula (I) and 3-nitro-4-(4-nitro-1,2,3-triazol-1-yl)furazan.

Abstract: The present invention relates to a process for determining the sensitive or insensitive nature of a crystalline hexogen. Said process comprises: the formulation of said crystalline hexogen in a matrix; the analysis of a sample of said matrix charged with said crystalline hexogen by differential scanning calorimetry; said matrix consisting essentially of at least one liquid polymer that is suitable for the formulation of binders for energetic materials charged with nitro organic explosives; and of at least one adsorbent for the volatile organic compounds, which is stable at the operating temperature of the analysis and which has low affinity for water. The present invention also relates to the crystalline hexogen in such a matrix.

Abstract: A method for producing propellant charges with progressive combustion characteristic and a higher charge density than previously considered possible to achieve, intended in the first instance for direct-firing barrel weapons such as tank cannons. Combined in the charge are at least two radially perforated propellant tubes, which are arranged in their entirety inside or after one another, and which have at an e-dimension selected in relation to the actual type of propellant and its desired combustion characteristic, combustion or ignition channels, and which have circular outer and inner boundary surfaces, in conjunction with which, before initiation of the charge, at least one of the total number of outer surfaces of these propellant tubes that are available for initiation has been treated with an inhibition, surface treatment or surface intended to delay the propagation of ignition to that surface so that the combustion of the propellant tubes is partially mutually overlapping.

Abstract: The present invention relates to a method of producing propellant charges (2) of multi-perforated stick propellant with maximized charge weights for sub-calibre, armour-piercing, high-velocity projectiles (3), which are provided, for example, with six to eight, fixed stabilizing fins (5-10). The invention also encompasses a multi-perforated stick propellant (11-12) intended for this purpose and a propellant charge produced from multi-perforated stick propellant according to the methods.

Abstract: The present invention relates to a method and an arrangement for the production of radially perforated, cylindrical propellant tubes (1, 23, 31). The invention is based on the underlying idea that the respective propellant tube (1, 23, 31) must be fixed and centred between its own open ends and thereafter to be perforated in stages in a large number of consecutive perforation operations by means of one or more pins (13) capable of displacement in a pin die (10) relative to the propellant tube towards and at least through the major proportion of the cylindrical wall of the propellant tube. Also included in the invention is the requirement for the displacement, between each perforation operation, of the propellant tube and the pin die (10) used for the preparation operation in such a way relative to one another that the propellant tube, after a complete perforation operation, shall be covered in its entirely by perforations (32, 33, 35, 36), which lie at a predetermined e-dimension distance from one another.

Abstract: The resent invention relates to a method for producing propellant charges with progressive combustion characteristic and a higher charge density than previously considered possible to achieve, intended in the first instance for direct-firing barrel weapons such as tank cannons.

Abstract: The present invention relates to a semi-continuous method for obtaining a composite explosive charge comprising a solid polyurethane matrix loaded with a charge, the charge being in powder form and comprising at least one nitro-organic explosive.

Abstract: The present invention relates to a semi-continuous method for obtaining a composite explosive charge comprising a solid polyurethane matrix loaded with a charge, the charge being in powder form and comprising at least one nitro-organic explosive.

Abstract: The present invention relates to a process for determining the sensitive or insensitive nature of a crystalline hexogen. Said process comprises: the formulation of said crystalline hexogen in a matrix; the analysis of a sample of said matrix charged with said crystalline hexogen by differential scanning calorimetry; said matrix consisting essentially of at least one liquid polymer that is suitable for the formulation of binders for energetic materials charged with nitro organic explosives; and of at least one adsorbent for the volatile organic compounds, which is stable at the operating temperature of the analysis and which has low affinity for water. The present invention also relates to the crystalline hexogen in such a matrix.

Abstract: The present invention relates to a method and a device for producing perforated propellant in the geometric form of block, stick, slab, cylindrical or tubular propellant (2) with high charge density and high progressivity. The propellant as claimed in the present invention is characterised by a large number of perforations, densely and evenly distributed over the entire propellant segments, made by perforation members (6) that are pressed down into the propellant. The perforations are thereby made in a plurality of steps with a predetermined step feed between each perforation operation. The device as claimed in the present invention also comprises a mobile pin die (5) away from but facing the feed path (1) for the propellant (2), and containing at least one row of pins for perforation of the propellant whereby each such row of pins comprises the number of pins (6) required to cover the complete width of the propellant segment across its direction of advance.

Abstract: The present invention relates to a method and a device for producing perforated propellant in the geometric form of block, stick, slab, cylindrical or tubular propellant (2) with high charge density and high progressivity. The propellant as claimed in the present invention is characterised by a large number of perforations, densely and evenly distributed over the entire propellant segments, made by perforation members (6) that are pressed down into the propellant. The perforations are thereby made in a plurality of steps with a predetermined step feed between each perforation operation. The device as claimed in the present invention also comprises a mobile pin die (5) away from but facing the feed path (1) for the propellant (2), and containing at least on one row of pins for perforation of the propellant whereby each such row of pins comprises the number of pins (6) required to cover the complete width of the propellant segment across its direction of advance.

Abstract: The present invention relates to a method and an arrangement for the production of radially perforated, cylindrical propellant tubes (1, 23, 31). The invention is based on the underlying idea that the respective propellant tube (1, 23, 31) must be fixed and centred between its own open ends and thereafter to be perforated in stages in a large number of consecutive perforation operations by means of one or more pins (13) capable of displacement in a pin die (10) relative to the propellant tube towards and at least through the major proportion of the cylindrical wall of the propellant tube. Also included in the invention is the requirement for the displacement, between each perforation operation, of the propellant tube and the pin die (10) used for the preparation operation in such a way relative to one another that the propellant tube, after a complete perforation operation, shall be covered in its entirely by perforations (32, 33, 35, 36), which lie at a predetermined e-dimension distance from one another.

Abstract: The resent invention relates to a method for producing propellant charges with progressive combustion characteristic and a higher charge density than previously considered possible to achieve, intended in the first instance for direct-firing barrel weapons such as tank cannons.

Abstract: In the military field of explosive munitions, a semi-continuous process produces a composite explosive charge composing a charged solid polyurethane matrix, the charge of which is pulverulent and comprise at least one nitro-organic explosive, by introduction into a mould of a pastry explosive composition and then thermal crosslinking of this composition. The composition is obtained by mixing constituents essentially comprising a polyol prepolymer, a plasticizer, a polyisocyanate monomer and a pulverulent solid charge comprising at least one nitro-organic explosive. This simple and economic process makes it possible to dispense, without disadvantage, with the pot life/curing time of the composition compromise.