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 method is provided for producing a large-calibre explosive projectile having a projectile casing with an ogival front part, which surrounds an internal area filled with a plastic-bonded explosive charge and, at a nose end, has a mouth closed by a nose fuze, wherein an elastic liner is arranged between the explosive charge and the inner wall of the projectile casing. The projectile casing is produced in two parts, such that, in the direction of the longitudinal axis of the projectile casing, a tail-end projectile casing section and an annular front projectile casing section, which contains the mouth, can be connected to one another in the area of the ogival front part, via a screw connection. The liner is introduced into the tail-end projectile casing section and the explosive charge is introduced into the liner before the two projectile casing sections are connected to one another.

Abstract: A method is provided for producing a large-calibre explosive projectile having a projectile casing with an ogival front part, which surrounds an internal area filled with a plastic-bonded explosive charge and, at a nose end, has a mouth closed by a nose fuze, wherein an elastic liner is arranged between the explosive charge and the inner wall of the projectile casing. The projectile casing is produced in two parts, such that, in the direction of the longitudinal axis of the projectile casing, a tail-end projectile casing section and an annular front projectile casing section, which contains the mouth, can be connected to one another in the area of the ogival front part, via a screw connection. The liner is introduced into the tail-end projectile casing section and the explosive charge is introduced into the liner before the two projectile casing sections are connected to one another.

Abstract: A method is provided for producing a large-calibre explosive projectile having a projectile casing with an ogival front part, which surrounds an internal area filled with a plastic-bonded explosive charge and, at a nose end, has a mouth closed by a nose fuze, wherein an elastic liner is arranged between the explosive charge and the inner wall of the projectile casing. The projectile casing is produced in two parts, such that, in the direction of the longitudinal axis of the projectile casing, a tail-end projectile casing section and an annular front projectile casing section, which contains the mouth, can be connected to one another in the area of the ogival front part, via a screw connection. The liner is introduced into the tail-end projectile casing section and the explosive charge is introduced into the liner before the two projectile casing sections are connected to one another.

Abstract: A method is provided for producing a large-calibre explosive projectile having a projectile casing with an ogival front part, which surrounds an internal area filled with a plastic-bonded explosive charge and, at a nose end, has a mouth closed by a nose fuze, wherein an elastic liner is arranged between the explosive charge and the inner wall of the projectile casing. The projectile casing is produced in two parts, such that, in the direction of the longitudinal axis of the projectile casing, a tail-end projectile casing section and an annular front projectile casing section, which contains the mouth, can be connected to one another in the area of the ogival front part, via a screw connection. The liner is introduced into the tail-end projectile casing section and the explosive charge is introduced into the liner before the two projectile casing sections are connected to one another.

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 projectile head is provided for a training cartridge having a propulsion unit, with an integrated projectile tail section, which can be used equally for training cartridges as well as combat cartridges of the same caliber size, wherein the projectile tail section is connectable to the projectile head with the aid of an extension on the projectile tail section, the extension is insertable into a receptacle in the projectile head, and the extension contains a recessed area, open on the front, for receiving a warhead detonator. The projectile head has a receptacle in the projectile head for receiving the extension of the projectile tail section, and an end stop which extends into the receptacle. The end stop is for contacting a warhead detonator present on the projectile tail section during assembly of the propulsion unit and the projectile head to prevent the extension from reaching a fully assembled position in the receptacle.

Abstract: A projectile head is provided for a training cartridge having a propulsion unit, with an integrated projectile tail section, which can be used equally for training cartridges as well as combat cartridges of the same caliber size, wherein the projectile tail section is connectable to the projectile head with the aid of an extension on the projectile tail section, the extension is insertable into a receptacle in the projectile head, and the extension contains a recessed area, open on the front, for receiving a warhead detonator. The projectile head has a receptacle in the projectile head for receiving the extension of the projectile tail section, and an end stop which extends into the receptacle. The end stop is for contacting a warhead detonator present on the projectile tail section during assembly of the propulsion unit and the projectile head to prevent the extension from reaching a fully assembled position in the receptacle.

Abstract: A missile includes a missile body and a guide assembly mounted on the missile body. The guide assembly has a plurality of pivots and a plurality of vanes mounted on respective pivots for a swinging motion between a folded position of rest and a deployed flight position. The vanes are arranged for free pivotal motion during flight in response to forces acting thereon to determine the flight position. In the folded position of each vane, its center of gravity is situated at a greater distance from the longitudinal axis of the missile body than the pivotal axis of the respective vanes. Abutments limit the flight position of the vanes to a maximum angle between the length dimension of the vanes and the longitudinal axis of the missile body. The maximum angle is greater than 90°.

Abstract: A missile includes a missile body and a guide assembly mounted on the missile body. The guide assembly has a plurality of pivots and a plurality of vanes mounted on respective pivots for a swinging motion between a folded position of rest and a deployed flight position. The vanes are arranged for free pivotal motion during flight in response to forces acting thereon to determine the flight position. In the folded position of each vane, its center of gravity is situated at a greater distance from the longitudinal axis of the missile body than the pivotal axis of the respective vanes. Abutments limit the flight position of the vanes to a maximum angle between the length dimension of the vanes and the longitudinal axis of the missile body. The maximum angle is greater than 90°.

Abstract: A missile includes a missile body and a guide assembly mounted on the missile body. The guide assembly has a plurality of pivots and a plurality of vanes mounted on respective pivots for a swinging motion between a folded position of rest and a deployed flight position. The vanes are arranged for free pivotal motion during flight in response to forces acting thereon to determine the flight position. Abutments limit the flight position of the vanes to a maximum angle between the length dimension of the vanes and the longitudinal axis of the missile body. The maximum angle is greater than 90°.