Abstract: An imaging device (2) for the stabilized imaging of an object onto a detector (14) with a first optical unit (4) and a second optical unit (6) and an optical element that is arranged between the optical units (4, 6) and can be moved for the purpose of stabilizing the imaging on the detector (14). For image stabilization in order to compensate for an undesirable wobbling movement of the imaging over the detector (14), the optical element is constituted of a micro-optical lens array (10).

Abstract: A camera system (2, 40, 50) including a sensor (12, 58) and a first optical system which includes a convex mirror (4, 42) and through which the image of a solid angle region (14) is producible on the sensor (12, 58) by way of a first beam path (18). In order, in addition to producing an image of a large solid angle region (14), to permit scanning or detailed representation of a smaller partial region (20, 66, 82) of the solid angle region (14), the camera system (2, 40, 50) includes a second optical system through which a partial region (20, 66, 82) of the solid angle region (14) is detectable by way of a second beam path (34, 60) on a detail sensor (68), wherein the detail region (20, 66, 82) is selectable by an optical element (28) which is movable relative to the sensors (12, 58, 68).

Abstract: An aircraft fuselage element (26) with a fuselage body (30) which forms an internal cavity (40) and which includes a viewing window (32, 34). To provide for taking substantially distortion-free high-resolution pictures in the infrared wavelength range and from a large angular range the fuselage body (30) is mounted for rotation about an axis of rotation (36).

Abstract: An airborne vehicle (1, 2, 10) which is equipped with an extinguishant container (12) for mist extinguishing is specified for efficient firefighting. A detonator (18) which is located on the extinguishant container (12) can be detonated via a fuze (19). The detonator (18) is attached to the airborne vehicle (1, 2, 10) such that, on firing the extinguishant which is contained in the extinguishant container (12) produces an extinguishant mist.

Abstract: A guided missile having a longitudinally extending airframe with a tip, a seeker head arranged in the tip and a window located in front of the seeker head for closing the airframe at the tip so as to protect the seeker head. A jettisonable protective cap consisting of at least two separable parts is attached to the airframe in front of the window for protection of the window.

Abstract: An apparatus for and a method of detecting a flight obstacle (28, 30, 32, 34) in the surroundings (50) of an aircraft (4), in particular for collision warning purposes, wherein images of the surroundings (50) are recorded, the flight obstacle (28, 30, 32, 34) is detected from the images and provided with an identification, and a signal (66, 68, 76) associated with the identification is outputted in a ground station (6). In order to guarantee a high level of certainty in respect to the control of the aircraft (4) which is effected automatically or by a ground control pilot it is proposed that detection and allocation of the identification are effected on board the aircraft (4) and the identification is sent to the ground station (6).

Abstract: A device for detecting attacking guided missiles with optical seeker head and for generating a laser beam directed to such guided missile has an all-around seeker with a detector responding to thermal radiation from the guided missile, and a laser which points to the guided missile detected by the all-around seeker. A roll and pitch gimbal system is provided. A roll gimbal is rotatable relative to the structure about a roll axis. A pitch gimbal is rotatable relative to the roll gimbal about a pitch axis orthogonal to the roll axis. The detector is structure-fixed. An imaging optical system is mounted on the roll and pitch gimbal system. The optical system with its optical axis can point to an object scenario. With each position of the gimbal system, an image of this object scenario is generated on the detector. The laser is also structure-fixed.

Abstract: A device for generating a laser beam in a LADAR system has a master oscillator with a laser-active medium and an amplifier stage in the form of a fiber optic power amplifier. This power amplifier amplifies the power of the oscillator. A carrier body is provided, on which a length of fiber of the power amplifier is coiled. The carrier body consists of a material of high thermal conductivity. The master oscillator may be a microchip laser. Diode lasers are used as pump light sources for the fiber optic power amplifier. This assembly can be made lightweight and compact, whereby it is particularly suitable for use in missiles.

Abstract: The invention relates to a method and a device for triggering a warhead in a target-tracking guided missile. The guided missile has an impact fuse and a proximity fuse for triggering detonation of the warhead. The invention triggers the warhead such that the damage caused to the target, such as an enemy fighter aircraft, becomes maximal. To this end, the miss disdance is predicted from influencing variabled detected during the flight of the guided missile. The warhead triggering delay time of the proximity fuse is set dependent on the predicted miss distance to achieve such maximum damage.

Abstract: In a method for detecting an image signal by means of an array (30) of photosensitive devices (10) with each of which the charge of a capacitance (12) can be altered, an optical signal (20) of each photosensitive device is first detected by means of the following substeps: creating a charge condition of the capacitance with a predetermined voltage (+U_DD), changing the charge of the capacitance (12) either with a photocurrent generated in the photosensitive device (10) by the optical signal (20) or with a quantity derived from the same and detecting the voltage across the capacitance (12) after a predetermined time period, deciding whether the detected voltage lies within a valid range and, if this is so, determining on the basis of the detected voltage a valid signal which characterizes the detected optical signal, and, if this is not so, repeating the cited steps with a time period which differs from the predetermined time period either a predetermined number of times or until it is determined that the

Abstract: An infrared seeker head for target tracking missiles has a main detector and an imaging optical system generating an image of a field of view on the main detector. The field of view contains a target such as an enemy aircraft. The missile is guided to the target in accordance with signals from the main detector. The target, if attacked by the missile, emits high-intensity laser radiation towards the missile as a counter-measure. This is to disturb the operation of the seeker head by dazzling or even destroying the main detector. The seeker head contains a device for defending against such disturbances. Various types of such defending devices are described. Incident light is deviated from the main detector. A second-quadrant-detector of reduced sensitivity guides the missile along the disturbing laser beam. Another embodiment uses attenuating optical elements in front of the main detector under the control of one or more second detectors.

Abstract: A RF antenna system mounted on, for example, a dielectric carrier plate is accommodated as a homing head in the front under a radome in a missile provided for locating radar systems or the like, in addition to other, further sensors potentially present in free spaces. The RF antenna system is composed of a three's or four's group of logarithmic-periodic crossed dipole antennas whose long axes proceed with optimized dimension obliquely relative to one another and that are interconnected with a monopulse feed network for taking aggregate and difference diagrams in azimuth and elevation. The antenna system for long-range missiles enables a monopulse position fixing in azimuthal or, respectively, elevational direction in an extremely broad frequency range.

Abstract: An external rotor comprises an annular case within which is the laminated stack forming the motor drive members and end members at each side of the stack. These are heat fitted together to form an annular blank which is then machined to form an axial bore therein and end faces normal to the bore. A stator laminated stack is heat fitted onto an axle and thereafter peripherally machined and bearing seats are machined on the ends of the axle. After the stator is inserted into the rotor bore, bearings are mounted on the ends of the axle and preloaded by tightening nuts onto the axle ends and against the bearings. The bearings comprise inner rings seated directly on the axle and outer rings seated directly on the inside and end faces of the rotor.