Abstract: The invention relates to a device for non-destructively material testing objects, in particular rims and wheels (12), comprising an X-ray inspection cabin (14) which contains an X-ray inspection device (28) for X-raying the objects and comprising conveyor devices (34, 36, 56, 68, 98) for conveying objects through at least one lock (20, 22) into the X-ray inspection cabin (14) and out of the X-ray inspection cabin (14). The aim of the invention is to prevent a leakage of X-rays into the surrounding area through the lock (20, 22) and to reduce the quantity of lead needed for shielding and optionally the space requirement of the device (10).

Abstract: The invention relates to a device for non-destructively material testing objects, in particular rims and wheels (12), comprising an X-ray inspection cabin (14) which contains an X-ray inspection device (28) for X-raying the objects and comprising conveyor devices (34, 36, 56, 68, 98) for conveying objects through at least one lock (20, 22) into the X-ray inspection cabin (14) and out of the X-ray inspection cabin (14). The aim of the invention is to prevent a leakage of X-rays into the surrounding area through the lock (20, 22) and to reduce the quantity of lead needed for shielding and optionally the space requirement of the device (10).

Abstract: The invention relates to a missile for combating stationary and/or moving targets comprising a seeker head (100), an effective charge which is arranged behind said seeker head in the direction of flight, a thruster such as a solid fuel booster having lateral outlet nozzles which is arranged behind the effective charge in the direction of flight, and a guiding section (104) which is arranged behind the thruster in the direction of flight. The guiding section comprises controllable aerofoils (105a, 105b) such as lateral and/or tail fins, and a guiding device. The missile also comprises a cruise engine (107) which is arranged on the tail, whereby the cruise engine is detachably connected to the guiding section by means of a first quick-acting closure (109a, 109b) such as a manually operable bayonet closure or the like.

Abstract: The invention relates to a method for combating near-surface and/or surface targets such as tanks or the like by using a missile comprising a seeker head, an effective charge and at least one thruster. According to the invention, the missile is redirected into an essentially horizontal cruising and seeking phase after completing an essentially vertical start phase. During said cruising and seeking phase, the missile scans the terrain ahead of it using the seeking head, whereupon an approaching phase which is directed in an essentially downward direction follows after the finally ensues head locks onto an identified target. An external reconnaissance system in an appropriate aircraft and/or spacecraft such as in a helicopter, a drone or in a satellite receives information for guiding the missile which is transmitted to the same.

Abstract: A missile for detecting and combatting enemy helicopters has an infrared homing head with an infrared lens and infrared sensor that will emit electrical signals, depending on incident infrared radiation, and the sensor is designed as a two-dimensional detector matrix consisting of a number of punctiform detector cells arranged essentially in the focal plane of the infrared lens. The homing head includes an arrangement for acquiring a target and determining the type of target from the target information by individually scanning each of the detector cells quickly one after another by evaluating the amplitude and frequency of the electrical signals. The determination includes determining the relative position of the target to the optical axis of the homing head and the homing head will then steer the missile to hit the target.