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: A bag assembly for the separation of a composite liquid into at least two components, comprises a set of bags and a bag-assembling device for assembling the set of bags. The set of bags comprises a separation bag connected by a product tube to at least one product bag. The bag-assembling device comprises a support member; a mounting means, connected to the support member, for removably mounting the bag-assembling device in a rotor of a centrifuge having a central cavity for containing the product bag; and a first securing means connected to the support member for releasably securing the product bag to the support member. The mounting means and the first securing means are so arranged that the product bag occupies a determined position in the central cavity of a rotor when the bag-assembling device in mounted therein.

Abstract: A pneumatic tire is capable of operation during underinflated condition and the construction of sidewalls are configured to compensate for negative cambers acting upon the tire. The inboard side of the tire is softened in comparison to the outboard side of the tire. This is achieved by either forming an asymmetrical tire in either the tire profile or the internal construction.

Abstract: A self-supporting pneumatic tire is molded in such a manner that ride comfort is improved, durability is increased, and a greater run-flat capability can be achieved. The self-supporting run-flat tire is molded such that the molded bead base width is equal or less than the rim width of the intended rim upon which the tire is to be mounted. By molding the tire with a bead width less than or equal to the rim width, the sidewall inserts are not subjected to additional stress during and after inflation of the tire and the strain energy is more evenly distributed through the sidewall pillar construction.

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.