Abstract: A missile includes a warhead accommodated in an inner space at a front portion of the missile; a ball joint being in alignment with the longitudinal missile axis and pivotally supporting the warhead; and an aiming device for placing the warhead into a desired pivotal orientation. The aiming device includes a plurality of inflatable vessels arranged axially adjacent the warhead in a distribution about the missile axis. Each vessel has a first end oriented toward the warhead and a second end oriented away therefrom. The vessels are supported at their second end by a disk situated in the inner space of the missile. A gas generator is coupled to each vessel for charging the vessel with a gas to place the vessel into its inflated state. In the inflated state each vessel exerts a torque on the warhead about the ball joint by an engagement between the first end of the respective vessel and the warhead. Further, an electronic control system is accommodated in the inner space of the vessel.

Abstract: A fin stabilized projectile for combatting a tank from above of the type including a rotating control unit disposed at the front of the projectile and containing a sensor for scanning the area to detect a target, and wherein the final phase of flying into the target is initiated by a force which acts on the tip of the projectile, particularly on the control unit. Since the control unit rotates relative to the warhead of the projectile to enable its sensor to detect the target, the gyro effect of this rotary movement generates pendulum movements in the projectile and thus causes deviations from the target at different target distances. To avoid yaw angles and lateral displacements of the projectile during the rotating-descending phase, a drive arrangement is provided within the projectile between the control unit and the warhead to impart an angular momentum to the warhead corresponding to the angular momentum of the control unit but directed in the opposite direction.

Abstract: The invention relates to a mine with at least one ejectable sub-munitions body disposed in a cup-shaped starting device and with a propulsion device for propelling the sub-munitions body into a selectable altitude range. For achieving that the propulsion device requires only a small structural volume, entails low cost because of the use of reduced amounts of propulsion charges and in addition operates safely and dependably. It has been proposed to dispose the propulsion device not in or on the sub-munitions body, but in the bottom part of the cup-shaped starting device. In this case the propulsion device advantageously consists of a high pressure chamber facing the bottom of the starting device, in which the propellant charge is contained, and of a low pressure chamber facing the sub-munitions body. The high pressure and low pressure chambers are separated from each other by a perforated plate provided with jets (holes).

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 projectile for a surface-to-surface weapon to combat a target from the top. The projectile includes a warhead; a propulsion system for accelerating the projectile directly after the projectile is placed in flight; a stabilizing guide assembly; a sensor for detecting a target in a longitudinal and lateral direction; and a pulse generator for turning the projectile about its center of gravity. The projectile additionally includes electronics for activating the warhead and for controlling the propulsion system and the pulse generator. A control unit rotates independently of the shaped charge warhead and houses the sensor, pulse generator and electronics. The pulse generator is arranged offset with respect to the sensor in the circumferential direction of the control unit.

Abstract: A fin stabilized subammunition body including a target detection device and being ejectable in a target area from a spin stabilized artillery carrier projectile. The target detection device includes a fixed sensor for detecting a target and producing target signals representing characteristics of the detected target, a reference platform for producing inertial reference signals, and a controller connected to the fixed sensor and the reference platform for producing drive control signals for selectively actuating a plurality of microreaction drive mechanisms arranged for producing transverse acceleration forces for aligning the body with a detected target.

Abstract: The invention relates to a projectile including a cylindrical receiving chamber (4) delimited by an interior wall (3) for a braking parachute (17) which can be ejected by way of a piston (9) that is longitudinally displaceable in the projectile, with the piston (9) being chargeable by an ignitable pyrotechnic charge (10). The braking parachute (17) is encased in a longitudinally divided sleeve (18) one side of which is in engagement with the piston (9). In order to completely or partially recover the projectile and not to impede deployment of the braking parachute (17), it is provided that the rear of the receiving chamber (4) is sealed by a cover (23) which can be ejected by way of the piston (9), is equipped with a rotational imbalance (26) and is in engagement with the other side of the sleeve (18). The braking parachute (17) is fastened to the piston (9).

Abstract: A projectile has at two parts (3, 4) axially arranged one behind the other and mutually linked, of which at least one contains a deployable parachute (6, 6'). In order to achieve a design that ensures a smooth and reliable separation of the parts (3, 4), followed by the deployment of the parachute (6, 6'), both parts (3, 4) are mutually linked by radial bolts (19) that can be radially actuated by the gas pressure generated by at least one pyrotechnic load (15) and radially moved by the gas pressure, thus separating the two parts (3, 4). The pyrotechnic load (15) can be ignited by a fuse (9).

Abstract: An improved warhead for transporting a plurality of useful loads which are disposed in a useful load chamber of the warhead. The warhead includes a casing in which a star-shaped hollow body is disposed. The hollow body acts as a brace for the structural assembly and has a central axial pressurized gas passage. The hollow body divides the useful load chamber into a plurality of cells in each one of which a useful load is mounted. Each cell also has an inflatable bag which is disposed radially inwardly relative to the useful load. Each inflatable bag is in fluid communication with the central axial pressurized gas passage and is adapted to expel the useful load transversely with respect to the direction of flight of the warhead upon receiving an internal or external command. Each leg of the star-shaped hollow body has longitudinally extending grooves in which a detonating charge is disposed for severing the casing.

Abstract: A process for controlling the flight attitude of a flying body and/or the activation of a useful live load on a flying body and the arrangement for carrying out the process. At least one receiving-emitting-unit for emitting and receiving energy in the form of ultra soundwaves is first emitted in bundled form from the unit and then reflected from the region immediately adjoining the flying body, for example, the ground surface, and received by the unit, whereupon the soundwaves are converted into electrical signals. By means of time lapse measurements of the emitted and reflected soundwaves there can, for example, be measured the distance of the flying body from the ground. If the flying body deviates from a predetermined flight path, control surfaces for correcting the flight path are adjusted by control means. Moreover, by means of the receiving-emitting-unit and via the control means a useful live load can be activated.

Abstract: A projectile to be fired from a tubular or rail-shaped launcher has a warhead integral with a rearwardly extending tube of smaller diameter which contains a propulsive charge inserted between the warhead and a sabot carrying a frangible inertial mass. The rear end of the tube has a constricted opening which, upon detonation of the charge, retains the rearwardly moving sabot while giving passage to the disintegrating mass as the projectile is propelled forwardly. The propulsion gases evolving within the tube are temporarily retained by one or more heat-destructible plugs in the sabot and/or in the tube which melt, burn or char to allow the delayed escape of the gases whereby an in-flight thrust is imparted to the projectile.