Abstract: A tail portion for a fin-stabilized projectile includes at least two deployable fins, which are inclined. The fins are arranged in at least two sections, which are arranged adjacent to another in the axial direction.

Abstract: A tail portion for a fin-stabilized projectile includes at least two deployable fins, which are inclined. The fins are arranged in at least two sections, which are arranged adjacent to another in the axial direction.

Abstract: The present invention relates to a method and a device for combating a pre-determined target with submunitions directed at the target from an airborne carrier in the form of a rocket, missile or equivalent (1) whereby the submunitions (17) are of the type whose main effect in target derives from impact with the target. As claimed in the present invention the submunitions (17) are given both a lateral motion vector (34) relative to the direction of flight of the carrier and a motion vector (35) in the direction of flight of the carrier. Jointly these motion vectors give the submunitions a resultant motion vector in a direction (36) towards the target.

Abstract: The present invention relates to a method and a device for combating a pre-determined target with submunitions directed at the target from an airborne carrier in the form of a rocket, missile or equivalent (1) whereby the submunitions (17) are of the type whose main effect in target derives from impact with the target. As claimed in the present invention the submunitions (17) are given both a lateral motion vector (34) relative to the direction of flight of the carrier and a motion vector (35) in the direction of flight of the carrier. Jointly these motion vectors give the submunitions a resultant motion vector in a direction (36) towards the target.

Abstract: A method and apparatus is for imparting, in a continuous sequence, a predetermined rotational movement to a warhead releasably housed in a protective canister and ejected out in ballistic ejection trajectories from the canister. The canister is spun to the desired rotational speed by flow of combustion gases through gas outlet nozzles discharging in the outer periphery of the canister and supplied from a central combustion chamber in which a propellant powder charge is combusted. The combustion gases are then led from the combustion chamber, in the final phase of the propellant charge combustion, through gas outlets facing towards the warhead and initially covered by the propellant charge and exposed as a result of the combustion, for ejecting the warhead out of the canister.

Abstract: An apparatus and method for separating a warhead to be delivered to a target from a carrier missile flying at high speed in a first aerodynamic trajectory include a rocket motor attached to the warhead in the carrier missile and an ejection tube positioned obliquely in the carrier missile rearwardly and upwardly with respect to a longitudinal axis of the carrier missile from which the warhead is ejected by the rocket motor into a second aerodynamic trajectory having a substantially higher maximum flight altitude then the first trajectory. The warhead is separated from the rocket motor after ejection by aerodynamic forces created from the angle of the ejection of the warhead from the carrier missile and the relative flight velocities of the warhead and the carrier missile. The aerodynamic forces act on a connection between the rocket motor and the warhead, whereby the motor and warhead upon the burnout of the motor follow separate forward trajectories upon separation.

Abstract: A sub-combat unit is arranged to be separated from a flying body over a target area, and includes a warhead, a target detector and two diametrically disposed carrier surfaces, each connected to a carrier arm and pivotally disposed about its own shaft located in a plane which is normal to the line of symmetry of the warhead and pivotable from a collapsed position in which the carrier arms and carrier surfaces connect to the circumferencial surface of the sub-combat unit, and to a position opened at 90.degree. at which both of the carrier surfaces form a retarding area for the fall velocity of the sub-combat unit and to impart to the sub-combat unit a rotation for scanning the target area in a helical pattern during the fall of the sub-combat unit towards the target area.

Abstract: A subwarhead which is adapted to be separated from a missile over a target area comprises an active part, a target detector and an aerofoil, the target detector and the aerofoil being pivotably mounted each on its own bearing shaft parallel with the line of symmetry of the active part in order to allow pivoting out of the target detector and of the aerofoil from a folded position to an unfolded position at the side of the active part in order to allow a controlled movement of scanning of the target area. Both the target detector and the aerofoil are provided with one or more displaceably arranged additional aerofoils for the purpose of increasing the braking area of the subwarhead in order to reduce the descent rate.

Abstract: The disclosure relates to a submunition disposed to be separated from an aeronautical body, for example a shell carrier canister or the like above a target area, the submunition essentially including a warhead (5), a target detector (6) and a device which imparts rotation to the submunition for scanning the target area in a helical pattern (4) during the fall of the submunition towards the target area. The target detector (6) is pivotally disposed on a carrying shaft (12a) parallel to the line of symmetry (5a) of the warhead in order to permit outward activation of the target detector (6) from a collapsed position where the optical axis of the target detector coincides with the line of symmetry (5a) of the warhead to an activated position where the optical axis of the target detector is parallel with the line of symmetry (5a) of the warhead, so as to permit free scanning vision for the target detector (6) beyond the warhead (5).

Abstract: A device for reducing the rotational speed of an ammunition unit, for instance a submunition unit, and at the same time imparting to the ammunition unit a lateral speed includes a body arranged to be swung out from the ammunition unit and be released in a specific outswung position. The body preferably consists of a band which is wrapped about the outer peripheral surface of the ammunition unit. One end of the band is fixed to the ammunition unit in such a way that the band is released in a specific outswung position.