Abstract: A projectile with several flare bodies, which are eccentrically housed in the body of the projectile and are ignited by at least one delay element for each flare body. The expulsion gases are conveyed from the ogive of the projectile to the delay elements through filler elements that form a channel in the center of the projectile for the expulsion gases.

Abstract: A spin-stabilized projectile with a guide band which is composed of at least two annular sub-guide bands that lie axially one behind the other is provided. An object of the invention is to ensure a durability of the connection between the multi-part guide band and the corresponding projectile body of the projectile even when high centrifugal forces act on the guide band, such as those centrifugal forces that occur in artillery projectiles. To achieve this, each of the sub-guide bands lies in a separate groove of the projectile.

Abstract: The invention relates to a warhead (10) for attacking particularly half-hard and/or soft targets, wherein the warhead comprises a splinter-forming casing (1) and an explosive material positioned in the casing (1). The warhead (10) further has a front plate (2) having a splinter formation, into which a distance sensor (3) is integrated. An igniter (5) for the explosive material and a stabilizing strap for adjusting perpendicular flight characteristics on the way to the target are located in the rear part of the warhead (10), wherein the initiation of the igniter (5) is determined by a property of the target to be attacked, namely, the parameter of a defined height from the target.

Abstract: In order to prevent slipping of the liner on an explosive charge in a missile, the invention provides that at least one flaring or cam is fixed in the liner which, when deformed inwards, can hook itself on the explosive charge.

Abstract: The invention relates to a warhead (10) for attacking particularly half-hard and/or soft targets, wherein the warhead comprises a splinter-forming casing (1) and an explosive material positioned in the casing (1). The warhead (10) further has a front plate (2) having a splinter formation, into which a distance sensor (3) is integrated. An igniter (5) for the explosive material and a stabilizing strap for adjusting perpendicular flight characteristics on the way to the target are located in the rear part of the warhead (10), wherein the initiation of the igniter (5) is determined by a property of the target to be attacked, namely, the parameter of a defined height from the target.

Abstract: In order to prevent slipping of the liner on an explosive charge in a missile, the invention provides that at least one flaring or cam is fixed in the liner which, when deformed inwards, can hook itself on the explosive charge.

Abstract: A projectile with several flare bodies, which are eccentrically housed in the body of the projectile and are ignited by at least one delay element for each flare body. The expulsion gases are conveyed from the ogive of the projectile to the delay elements through filler elements that form a channel in the center of the projectile for the expulsion gases.

Abstract: A gas pressure switch is provided for an ignition and safety system for ammunition. The switch includes a housing; a piston actuator within the housing, the piston actuator being displaceable from an idle position to a contacting position by propellant gases of the ammunition during use; at least two contact pins that are attached immovably to the housing; a contacting device operatively associated with the piston actuator and located on a first side of the piston actuator, the first side being opposite a second side on which the propellant gases act during use, the contacting device connecting electrically to the contact pins when the piston actuator is in the contacting position; and a locking pin which holds the piston actuator in the idle position until a predetermined gas pressure is reached and which shears off when the predetermined gas pressure is reached, so that the piston actuator can be displaced into the contacting position.

Abstract: A lateral thrust control is provided for influencing the flight trajectory of a projectile. The control has a main control unit; a central, axially extending main recess in the main control unit; a plurality of thruster recesses in the main control unit for accepting correction thrusters; an ignition element for one of the correction thrusters disposed in each of the thruster recesses; and at least one tubular conductor support of an electrically insulating material arranged inside the main recess of main control unit. At least some of the electrical conductors are in the form of conductive tracks fixedly arranged on the at least one tubular conductor support such that a particular contact element for a particular ignition element contacts the conductive track assigned to the particular contact element.

Abstract: A gas pressure switch is provided for an ignition and safety system for ammunition. The switch includes a housing; a piston actuator within the housing, the piston actuator being displaceable from an idle position to a contacting position by propellant gases of the ammunition during use; at least two contact pins that are attached immovably to the housing; a contacting device operatively associated with the piston actuator and located on a first side of the piston actuator, the first side being opposite a second side on which the propellant gases act during use, the contacting device connecting electrically to the contact pins when the piston actuator is in the contacting position; and a locking pin which holds the piston actuator in the idle position until a predetermined gas pressure is reached and which shears off when the predetermined gas pressure is reached, so that the piston actuator can be displaced into the contacting position.

Abstract: The invention relates to a device for guiding a missile (1; 30) with a missile tip (2) and a cylindrical section (3) adjoining the tip of the missile; the device is provided with at least one control block (4; 31, 32) with exhaust openings (13-15) of corresponding nozzle bodies (10-12) arranged perpendicularly in relation to the missile's surface.In order to accomplish effective guidance, particularly of high-speed missiles (1; 30), in a simple and cost-effective manner it is proposed that the control block (4; 31, 32) be constructed with a plurality of small, fast-burning rocket motors (7-9; 33-36) that are arranged radially on the missile's periphery (1; 30) and that are ignitable in a predeterminable sequence and number.

Abstract: A propellant-charge pack has an annular envelope having an outer wall extending along and centered on an axis, a pair of axially spaced end walls extending transversely inward from the axis and having inner peripheries centered on the axis, and an inner wall defining a clear axially throughgoing passage between the inner peripheries of the end walls. The envelope is generally axially symmetrical about the axis, that is it is formed as a body of revolution or of regular polygonal section, and is substantially symmetrical to a plane perpendicular to the axis midway between the end walls. A relatively easily ignited primar charge forms a part of the inner wall symmetrical of the plane and a propellant charge fills the envelope between the walls outward of the inner wall. The primar charge is of such high combustibility, compared to the diameter of the passage, that the entire primar charge, even of a stack of such packs, will be ignited before they burn through and set off the respective propellant charges.

Abstract: A propellant-charge pack has an annular envelope having an outer wall extending along and centered on an axis, a pair of axially spaced end walls extending transversely inward from the axis and having inner peripheries centered on the axis, and an inner wall defining a clear axially throughgoing passage between the inner peripheries of the end walls. The envelope is generally axially symmetrical about the axis, that is it is formed as a body of revolution or of regular polygonal section, and is substantially symmetrical to a plane perpendicular to the axis midway between the end walls. A relatively easily ignited primer charge forms a part of the inner wall symmetrical of the plane and a propellant charge fills the envelope between the walls outward of the inner wall. The primer charge is of such high combustibility, compared to the diameter of the passage, that the entire primer charge, even of a stack of such packs, will be ignited before they burn through and set off the respective propellant charges.

Abstract: A vane assembly for a projectile has a carrier carrying a plurality of pivots, having at the pivots respective carrier elements, and adapted to be secured to an end of the projectile. Respective vane elements are each pivotal on the pivots between an inner position lying immediately adjacent the respective carrier element and within a projection of the projectile and an outer deployed position projecting beyond the projection. Respective heat-destructible pins engaged between the vane elements and the respective carrier elements normally retain the vanes in the inner position and release the vanes for movement into the outer position when destroyed by heat. The carrier element is a rib of the carrier against which the respective vane lies when not deployed.

Abstract: The target-effective mass of cartridged ammunition is increased while maintaining a predetermined cartridge length.A projectile body has a projectile tail portion extending rearwardly on which a fin or wing-stabilization arrangement is mounted. This tail portion extends rearwardly towards the immediate vicinity of the propellant charge casing bottom. A projection extends rearwardly past the wing or fin-stabilization guide arrangement. This projection includes a massive portion which separates at firing from the propellant charge casing bottom. The rear portion of the projectile body is surrounded by a sheathing of combustible material forming the ignition element which sheathing extends from the cartridge case bottom up to at least the middle of the propellant charge casing and has a longitudinal extent l.sub.2.

Abstract: A multi-range ammunition unit for firing at a high angle and with preselected muzzle velocities. The ammunition unit includes at least two partial propellant charges, a first one of which is fixedly mounted to the bottom of the shell casing and the second one or ones of which are fixedly mounted to the bottom of the projectile of the ammunition unit. All partial propellant charges are coaxially arranged with respect to the shell casing. Mechanical and/or electrical ignition means are provided to first ignite the first propellant charge and then selectively sequentially ignite the second propellant charge or charges.

Abstract: A charge formed of a mass of packed propellant is generally centered on an axis and is of radially generally uniformly and radially outwardly increasing density. This charge has a predetermined size and shape and is made by first filling particulate propellant into a chamber centered on an axis and defined by side walls extending at least generally parallel to the axis. This chamber is radially somewhat larger than the predetermined size and shape for the charge. At least some of the side walls are then displaced radially inward to reduce the volume of the chamber until the reduced chamber generally has the size and shape for the charge. The weight of the particulate propellant filled into the chamber is equal to the desired weight for the charge. The tail of a projectile is positioned in the chamber before filling the particulate propellant into the chamber. The projectile downwardly closes the chamber and can be raised after the mass is packed to push it up out of the chamber.