Abstract: A projectile in which the metallic base body itself is used as a ground wire and only the signal line is passed through the inside of the base body so that it is insulated by a suitable bore of the base body. The signal line is insulated from the ground wire by a coating of an electrically insulating material applied to the base body, before the signal line is introduced into the bore. The two ends of the signal line are provided with connecting contacts, which preferably can be screwed at least partially into the base body and are mounted in such a way that they are insulated from the base body. To allow contacting of the ground wire, which is formed by the base body itself, the front end and the rear end of the base body are provided with coating-free blind bores.

Abstract: The invention relates to so-called fuze damping in projectiles, in particular, those provided with a built-in firing delay. Thus, a projectile (1) is provided having a rear part (1a) and a fuze (2), wherein at least one damping element (7) is inserted between a fuze base (5) and the projectile (1) and/or between a fuze shoulder (6) and a possible threaded ring (4), or similar attachment element. The damping element (7) is in the form of a disc, ring or pot, and is composed of a material with a lower acoustic impedance than the material of the projectile (1).

Abstract: The invention relates to a primer element, in particular for ammunition or similar, comprising at least one primer composition that has at least one sleeve acting as the housing for the primer element, at least one contact pin and a mass contact. Multiple wires, (at least two) are used, one end of said wires being connected to the contact pin and the other end of said wires to the mass contact. The multiple wires are embedded in the primer composition(s).

Abstract: The invention relates to a so-called fuze damping in projectiles, in particular with a built-in firing delay. The invention proposes a projectile (1) having a rear part (1a) and a fuze (2) , wherein at least one damping element (7) is inserted between a fuze base (5) and the projectile (1) and/or between a fuze shoulder (6) and a possible threaded ring (4) or similar attachment element. The damping element (7) is in the form of a disc, ring or pot, and is composed of a material with a lower acoustic impedance than the material of the projectile (1).

Abstract: A projectile in which the metallic base body itself is used as a ground wire and only the signal line is passed through the inside of the base body so that it is insulated by a suitable bore of the base body. The signal line is insulated from the ground wire by a coating of an electrically insulating material applied to the base body, before the signal line is introduced into the bore. The two ends of the signal line are provided with connecting contacts, which preferably can be screwed at least partially into the base body and are mounted in such a way that they are insulated from the base body. To allow contacting of the ground wire, which is formed by the base body itself, the front end and the rear end of the base body are provided with coating-free blind bores.

Abstract: The invention relates to a primer element, in particular for ammunition or similar, comprising at least one primer composition that has at least one sleeve acting as the housing for the primer element, at least one contact pin and a mass contact. Multiple wires, (at least two) are used, one end of said wires being connected to the contact pin and the other end of said wires to the mass contact. The multiple wires are embedded in the primer composition(s).

Abstract: A separating device is integrated in ammunition, with which a line is separated at the earliest possible time during a firing process. The separating device is composed mainly of a piston, which preferably has a sharp edge, is guided in a rigidly mounted cylinder, and, in the unloaded state, is positioned by a shear flange. The cable is preferably securely supported in a protective tube which is connected with a propellant charge primer, and in which the cable is guided as far as the tip of the propellant charge primer and is then further guided to the rear end of the projectile. In the upper area of the cylinder, the cable is guided through a bore, which preferably lies transversely to the direction of acceleration of the piston, so that when the piston moves forward, the cable is separated by the sharp edge of the piston.

Abstract: A separating device is integrated in ammunition, with which a line is separated at the earliest possible time during a firing process. The separating device is composed mainly of a piston, which preferably has a sharp edge, is guided in a rigidly mounted cylinder, and, in the unloaded state, is positioned by a shear flange. The cable is preferably securely supported in a protective tube which is connected with a propellant charge primer, and in which the cable is guided as far as the tip of the propellant charge primer and is then further guided to the rear end of the projectile. In the upper area of the cylinder, the cable is guided through a bore, which preferably lies transversely to the direction of acceleration of the piston, so that when the piston moves forward, the cable is separated by the sharp edge of the piston.

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 cartridge, comprising a cartridge case (3), a projectile (4), a propellant charge igniter (8) extending in the direction of the longitudinal axis of cartridge (1) and arranged inside the cartridge case (3), and an electrically programmable projectile fuse arranged in the projectile (4) and connected via at least one electrical line (110) to an electrode on the cartridge base (2). The cartridge case (3) comprises at least two case sections (5, 6) with at least one separation location in the region between the front end (7) of the propellant charge igniter (8) and the projectile tail (9) for the installation of a section of the electrical line (110) between the cartridge base (2) and the projectile fuse using two rotating connector assemblies, one of which turns more easily than the other.

Abstract: A cartridge, comprising a cartridge case (3), a projectile (4), a propellant charge igniter (8) extending in the direction of the longitudinal axis of cartridge (1) and arranged inside the cartridge case (3), and an electrically programmable projectile fuse arranged in the projectile (4) and connected via at least one electrical line (110) to an electrode on the cartridge base (2). The cartridge case (3) comprises at least two case sections (5, 6) with at least one separation location in the region between the front end (7) of the propellant charge igniter (8) and the projectile tail (9) for the installation of a section of the electrical line (110) between the cartridge base (2) and the projectile fuse using two rotating connector assemblies, one of which turns more easily than the other.

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 fin-stabilized projectile includes a projectile body having a rear portion defining a rearwardly open cavity and a stabilizing assembly which has an axially slidable fin support in the cavity. The fin support has a retracted position in which the fin support is withdrawn into the cavity and an outwardly shifted position in which the fin support projects from the projectile body. A plurality of fins are pivotally held in the fin support. Each fin has a folded state in which it is withdrawn in the fin support when the latter is in the retracted position and a deployed state in which it is unfolded and extends substantially externally of the fin support when the latter is in its outwardly shifted position. When the projectile has left the weapon barrel, the fin support is axially shifted and the fins move into the deployed state.

Abstract: A case base (1; 1′) for large-caliber ammunition, in which the case jacket (2) comprises a combustible material, with the case base (1; 1′) comprising a metallic base plate (3) and a support ring (4; 4′) that projects axially beyond the surface of the base plate (3) at its edge, and an elastomer or thermoplastic obturation ring (5; 5′) that is disposed on the projectile side of the support ring (4; 4′). In order for the obturation ring (5; 5′) to be secured simply to the support ring (4; 4′) and removed again after the ammunition has been fired, the support ring (4; 4′) has, on its inner surface (6) facing the obturation ring (5; 5′), a groove-shaped undercut (7), into which the end (8) of the obturation ring (5; 5′) that faces the support ring (4; 4′) extends with a form-fit and/or positive lockup.

Abstract: A projectile to be fired from a weapon barrel includes a projectile body and a plurality of stabilizing wings circumferentially distributed about a rearward portion of the projectile body. A pin pivotally attaches each stabilizing wing to the projectile body for pivotal motion about a pivot axis to assume a folded state and an outwardly pivoted, deployed state. In the folded state of the stabilizing wings the center of gravity of the respective stabilizing wings is at a greater radial distance from the longitudinal axis of the projectile body than the pivot axis. A gliding body is releasably mounted on each stabilizing wing. Each gliding body has a wing-shaped extension for contacting an inner surface of the barrel in the folded state of the stabilizing wings as the projectile travels in the barrel upon firing.

Abstract: A fin-stabilized projectile includes a projectile body having a rear portion defining a rearwardly open cavity and a stabilizing assembly which has an axially slidable tin support in the cavity. The fin support has a retracted position in which the fin support is withdrawn into the cavity and an outwardly shifted position in which the fin support projects from the projectile body. A plurality of fins are pivotally held in the fin support. Each fin has a folded state in which it is withdrawn in the fin support when the latter is in the retracted posit on and a deployed state in which it is unfolded and extends substantially externally of the fin support when the latter is in its outwardly shifted position. When the projectile has left the weapon barrel, the fin support is axially shifted and the fins move into the deployed state.

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°.

Abstract: A tandem warhead for combatting actively armored targets including two shaped or projectile forming charges arranged one behind the other, and an ignition or firing delay unit which causes the ignition of the first charge and then the second charge with a time delay. To avoid the target's active armor plate (which moves when hit by the first charge, from impeding or even destroying the following charge) the tandem warhead is provided with a device for determining the actual angle of the warhead relative to the target, i.e., the firing or attack angle, and an ignition time delay .DELTA.t associated with the respective firing angle .alpha.. To determine the firing angle .alpha., an angle determining device includes a plurality, preferably four, distance measuring devices with which respective distance coordinates between the tandem warhead and the target are measured and used for determining the momentary firing angle .alpha.. Thereafter, the delay time .DELTA.

Abstract: An improved liner for a warhead having a shaped explosive charge for the production of a projectile by explosive reshaping of the liner includes a liner body having a central region which has a radius of curvature which is smaller than that of a surrounding liner portion. The central region of the liner is indented relative to the surrounding liner portion along a central axis of the liner body toward the side of the liner adjacent the shaped explosive charge. Upon explosive reshaping of the liner, a projectile having an ogival shape is produced.

Abstract: A warhead for enclosing an explosive charge includes a casing for surrounding the charge. The casing has an end presenting a frontal face. A liner having a circumferential area for attachment to the end of the casing and a coefficient of thermal expansion .alpha..sub.R is fastened to the casing by way of an intermediate ring connected to the circumferential area of the liner. The intermediate ring has a portion which is brought around the frontal face of the casing and which has a pressure face which presses against the exterior of the casing. The liner has a coefficient of thermal expansion .alpha..sub.E which is at least as great as the coefficient of thermal expansion .alpha..sub.R of the intermediate ring.