Abstract: A proximity sensor (11) is intended to initiate the warhead of a defence shell which is fired against an attacking projectile from the object to be protected in order to interfere with or even destroy the functionality of the attacker. For that purpose the proximity sensor (11) should not yet respond to the attacker which is to be defended against by the shell appearing ahead in the direction of flight thereof; rather, the proximity sensor is to respond only when the attacker to be defended against is detected ahead inclinedly at an operatively optimal distance. Such a response characteristic in the form of the wall of a hollow cone is afforded if an annular detector element (12) is arranged in the image focus plane behind a positive cylindrical lens (14).

Abstract: A blast shell is launched as a defense against an attacking tail fin-stabilized projectile, such as in particular a KE penetrator, from an object which is to be protected. Gas fumes and a reaction pressure blast wave from a fired blast warhead of the shell act principally on the tail region of the attacking projectile and thereby deflect the latter from a trajectory in the attack direction so that the object under attack is either missed or at least is not hit in a head-on direction, thereby reducing the effectiveness of the attacking projectile.

Abstract: Described is a system (10) for protecting a target such as an armoured vehicle, a bunker or the like from missiles. The protective system (10) has a launching container (12) with at least one launching tube (36) for an associated fragmentation projectile (38), mounted adjustably on a base portion (14). A sensor arrangement (26, 28) is provided for detecting the target to be combatted and aligning the launching container (12) with the target to be combatted. A control device (32) for a drive arrangement (24) is connected together with the sensor arrangement (26, 28) by way of a signal processing device (30). The drive arrangement (24) serves for aligning the launching container (12) with respect to the base portion (14). The/each fragmentation projectile has a special fragmentation filling (40) and a fuse device (44) for controlling the time of detonation.

Abstract: In a protection arrangement for affording protection from projectiles (13) attacking armoured vehicles (11) such as in particular combat tanks catapult-type plate modules (18) are no longer carried directly by the structure of the vehicle (11) to be protected but by a front mounting (17) which is of comparatively lightweight structure but which is rigid in respect of deformation by virtue of strut structure means of a three-dimensional framework-like configuration and which in particular is mounted in front of the front (16) of a combat tank body (12) but which can also be provided therearound.

Abstract: An artillery rocket including a motor for the launching thereof into a ballistic trajectory across a specified target area over which a payload is to be released. The rocket is equipped with a flight controller or autopilot for the control over a rudder or control surface-setting or control system which is actuatable from a navigational receiver with actual positional coordinates. The flight controller operates on a control or setting system which is disposed in front of the warhead in the forward region of the nose cone without noticeably restricting the usable volume for the warhead.

Abstract: An installation for the measurement of the wind direction and the wind velocity of a ground wind dependent upon the altitude above the ground. More particularly, the installation is employed for improving the hitting accuracy of unguided projectiles or rockets. The installation incorporates a vertically-orientable firing barrel or launching tube for the launch or firing of a measuring projectile, a speed measuring installation for the measurement of the launching speed of the measuring projectile from the launching tube, an optical camera device for the photographing and digitalizing of successive pictures of the measuring projectile which is fired from the launching tube taken in timed sequence.

Abstract: An airborne submunition member having mountings or holders for glide wings arranged offset relative to each other exteriorly on the trunk or body of the airborne member, from which mountings glide wings are outwardly extendable, which are retracted into the glide wing mountings in the transport position of the member. At least one of the glide wing mountings or holders is supported on the trunk of the airborne submunition member so as to be pivotable or revolvable about the longitudinal axis thereof, and in the transport position is pivoted or rotated towards one of the other glide wing mountings.

Abstract: A projectile, an airborne body or a missile, such as an article of ammunition, having extendable wings, whereby a wing covering is provided to extend between a front spar which is extendable through the action of a power element, and a rear spar which is retractable with its outer end against the front spar, as well as providing for a specially adapted power element for this purpose. The power element has one end thereof engaging at the front spar and has its opposite end engaging against a slider which is latched to the projectile so as to be supported thereon for displacement along the longitudinal direction, and wherein the rear spar has its inner end pivotable in front of the slider in the direction of displacement thereof, and upon the slider being unlatched, is pivotable further by the slider under the action of the power element for effectuating the tensioning of the wing covering.

Abstract: A flying body for subordinate-ammunition missile with extendable glide wings. The flying body or missile of the above-mentioned type has the wings pivotally retained in attachments which are arranged generally in parallel with the longitudinal axis of the missile on the casing of the fuselage of the missile, and which are equipped with longitudinal grooves each respectively stowing a retracted wing.

Abstract: A projectile possessing extendable wings or fins which are adapted to be pivoted radially outwardly of the projectile. The wing or fin includes a flexible covering and a tensioning device; for example, a strut arrangement, and with the wing or fin being displaceable from a retracted position prior to launch of the projectile to an outwardly extended position in which the applicable covering portion is tensioned by the tensioning device so as to thereby provide a stable, predetermined aerodynamically defined wing or fin configuration.