Abstract: A device is provided for reducing the rate of rotation of a spinning submunition unit having a tail end provided with a deployable braking device, from a time after the submunition unit is ejected from a spin stabilized carrier projectile until the braking device is deployed. The device includes a plurality of bands arranged to form a star-shaped symmetrical band structure for placement around the braking device. Each of the bands has a free end provided with a wind pocket.

Abstract: A deceleration device for a submunition unit includes a cartridge releasably attached to the submunition unit. A releasable package including at least one pocket is disposed in the cartridge and is connected to the cartridge by a packaging line. An auxiliary parachute and a rotation parachute are disposed in the cartridge, with at least the rotation parachute being accommodated in the at least one pocket of the releasable package and the auxiliary parachute being disposed in a pocket separate from the at least one pocket. The auxiliary parachute is connected to the cartridge and the rotation parachute is connected to the submunition unit. A deployment mechanism causes the auxiliary parachute to be deployed in advance of the rotation parachute after the cartridge is released from the submunition unit and the rotation parachute to be deployed after the cartridge is decelerated by the auxiliary parachute for decelerating the submunition unit.

Abstract: A deceleration element is provided for attachment to a tail end of a submunition unit for deployment when the submunition unit is ejected from a spin stabilized carrier projectile for reducing velocity and spin of the submunition unit. The deceleration element includes two approximately circular, air-tight, planar textile fabric layers of essentially the same size having a diameter exceeding the diameter of the submunition unit and circumferentially sewn together to form an inflatable interior between the two fabric layers. The fabric layer disposed closest to the tail end of the submunition unit is clamped by fasteners to the tail end of the submunition unit and has a front side facing the tail end of the submunition unit for encountering air when the deceleration unit is deployed. At least four air capture pockets are disposed at the front side of the one fabric layer and are distributed at regular intervals in a circumferential direction.

Abstract: A deceleration device for a submunition unit ejectable from a spin stabilized carrier projectile includes a deployable deceleration element. The deceleration element is packaged in textile package including an essentially circular disc, at least three straps connected and arranged radially to the disc, with each strap having a free end and provided with a loop and a closing line received through the loops for pulling the loops together to close the package about the deceleration element. An activation line is connected to the closing line and held by the textile package for releasing the closing line for allowing the package to open for deployment of the deceleration element after the activation line is released from the package by being stretched in a controlled manner.

Abstract: An arrangement for ejecting objects from a projectile, includes a hollow projectile body having a nose end with a plurality of objects disposed in a column within the projectile body. An ejection charge is disposed within the projectile body at the nose end. An ejection device including a hood enclosing a cavity is ejectably disposed within the projectile body between the ejection charge and the column. The hood has a wall with an opening facing the ejection charge so that, after ignition of the ejection charge, resulting powder gases enter into the cavity through the opening to generate a gas pressure between the hood and the adjacent object and simultaneously exert a force on an exterior portion of the wall of the hood that causes the hood and the column to be ejected from the tail end of the projectile body, whereby the hood separates from the column once the hood and column are free of the projectile due to the pressure in the cavity.

Abstract: A rotary parachute includes a canopy having an apex and comprised of triangular, sewn-together fabric segments each having a base edge along an outer circumference of the canopy, a tip opposite the base edge and longitudinal edges on either side of said tip with seams connecting together the adjacent longitudinal edges of adjacent segments and rotation slits existing in regions of the respective seams. The tip of each segment is offset laterally from the apex of the canopy to form an apex opening in the canopy having a shape of a regular polygon and the base edges are offset from one another so that each segment has a circumferentially projecting tip.

Abstract: A submunition unit for a spin stabilized carrier projectile (1), with the submunition unit including an antenna disposed at the nose of its casing (7), and with the antenna (5) being covered by a protective cover (6). The casing (7) and the protective cover (6) are provided with respective axially overlapping collars (8, 9) which are each provided with respective opposed circumferential grooves (14, 15) to form an annular recess to accommodate an elastic securing ring (16). The securing ring, which is normally positioned within the innermost of the circumferential grooves, expands under the influence of centrifugal forces to connect the casing and protective cover together in a form-locking manner.