Abstract: The invention relates to a housing for electronical components for two- or multi-channel systems. The housing includes a housing frame, which is separated by electrical screens into two or several electrically screened parts. At least two covers are detachably attached to the housing frame. The covers permit access to the electrically screened parts of the housing frame. Electronical components associated with each channel are arranged in a respective one of the electrically screened parts of the housing. It is possible to accommodate some of the electronical components in the covers. The covers can be provided with connectors.

Abstract: An all-around observation device is provided for detecting a field of view having a large solid angle. The all-around observation device comprises an imaging optical system having objective means continuously rotating with a first rotary speed about a first axis and having a rotating imaging path of rays, and a polygon wheel rotating with a second rotary speed and being located in the rotating imaging path of rays. The polygon wheel is provided with beam deflecting means for continuously deflecting the imaging path of rays each time said rotating imaging path of rays passes one polygon face of the polygon wheel, such that a field of view sector is stationary imaged during a finite observation time on a detector having a two-dimensional arrangement of detector elements. A motor is arranged to continuously rotate, with a third rotary speed, the polygon wheel and the objective means about a second axis, which forms an angle with the first axis.

Abstract: A hanger assembly for missiles, in which a hanger, with opposite carrying rails to guide the missile in a launcher, is connected to the missile by means of a screwed connection. The hanger is screwed from the outside, with screws to a enlargement or increased thickness portion (16,60). Preferably a clamp, provided with a enlargement or increased thickness portion surrounds the airframe (Zelle) of the missile and is fixed thereto. The screw connection of the hanger is effected with screws the axes of which form an angle with the plane of the carrying rails.

Abstract: The invention relates to an arrangement for shifting optical images between individual channels. A plurality of imaging optical systems adapted to image conjugately upon each other, in an associated shiftable optical channel, an associated plane and an intermediate image plane, comprise a micro-mechanical mirror system (mirror array) arranged in the intermediate image plane and having a grid of mirror elements adapted to be tilted and actuated. A further imaging optical system is adapted to image conjugately upon each other, in a common channel, the intermediate image plane and a plane associated with the common channel. The mirror elements of the micro-mechanical system are adapted to be actuated in such a manner, that they optically connect optionally one of the shiftable channels to the common channel.

Abstract: A torquer assembly is to exert torques about two mutually orthogonal axes on a platform which is mounted for universal movement about a central swivelling point. To this end, a stator having four pairs of pole pieces is provided. The pole pieces are angularly spaced by 90.degree. about an axis passing through the swivelling point. The pole pieces of each pair define an air gap therebetween. The air gap is limited by spherical surfaces. The spherical surfaces are curved about the swivelling point. Permanent magnets together with the pole pieces and magnetic return loops form magnetic circuits, a magnetic field being generated in the air gaps. An armature with four elongated, arcuate coils angularly offset with respect to each other by 90.degree. is connected with the platform. The coils have circumferentially extending turns. Each of these coils extends, with an arcuate coil section, into the air gap of a respective one of the pairs of pole pieces.

Abstract: A locking assembly in a launcher for missiles comprises a pivotally mounted blocking latch which is provided with two blocking lugs for extending over a shoe provided on the missile. The blocking latch is biased by a spring toward a blocking position, in which the shoe of the missile is retained by the blocking lugs. A locking lug is provided on the blocking latch. In the blocking position the locking lug engages a safety lever having a contact surface, when inertial forces of the missile act on the blocking latch such that the blocking latch is retained in the blocking position, in which the blocking lugs extend over the shoe of the missile. The safety lever is pivotable about a pivot axis out of the pivotal path of the locking lug. The safety lever comprises means for reducing the distance between the contact surface and the pivot axis during the pivotal movement of the safety lever, such that the contact surface is removed from the locking lug during the pivotal movement.

Abstract: In a tube connection, particularly for connecting two tubular elements of the airframe of a substantially tubular a missile, the tubular elements to be interconnected have end portions of substantially identical shapes. Each end portion has a smaller-diameter first circumferential section extending through substantially 180.degree. and a larger-diameter second circumferential section also extending through substantially 180.degree.. The larger-diameter circumferential section of each tubular element overlies the smaller-diameter circumferential section of the other tubular element. The circumferential sections are provided with radial bores for connection screws. Arcuate elements having threaded bores are arranged inside the thus interconnected circumferential sections. These threaded bores are aligned with the radial bores of the circumferential sections and threadedly receive the connecting screws.

Abstract: A seeker head comprises a seeker for scanning field of view and a gyro assembly sensing attitude variations. Signal processing means process information from two consecutive scans of the seeker. The signals from the gyro assembly are applied to a coordinate transformer circuit, which transforms the picture information from consecutive scans into a common intertial coordinate system. A target is selected by target selection logic. The coordinates of a selected target are read into a deviation memory. The signal processing means provide the inertial sight line rate of the sight line to a selected target. After each scanning and signal processing cycle the location is computed at which the target is to be expected according to the sight line rate measured during the preceding cycle. This permits comparison of target signals in consecutive scans even with moving targets, recovery of temporarily lost targets and discrimination between actual targets, such as an aircraft, and mocktargets, such as flares.

Abstract: A hanger of steel for guiding a missile in a launcher has arcuate flanges matching the shape of the missile an a guiding element of substantially T-shaped cross section. A longitudinal recess is defined on the outer side of the transverse bar of the "T". The surfaces of the transverse bar facing the flanges define rest surfaces and the adjacent lateral surfaces of the vertikal bar of the "T" serve as lateral guiding surfaces for the missile. A longitudinal, rounded recess is provided between each of the lateral surfaces and the adjacent rest surface, in order to increase the notch radius. The surface of the material is treated to generate internal compressive stress in the regions of the recesses.

Abstract: In a seeker head for target tracking missiles or projectiles, an imaging optical system with an optical axis is mounted on a rotor. The rotor is mounted for universal swivelling motion in the missile. It rotates about its geometrical axis. Thereby, the rotor is stabilized in inertial space as a gyro. The optical system images an object scene on a circular array of detector elements. The rotor can be caused to make controlled precession and nutation movements by control loops with attitude pick-offs and a torquer coil such that the optical axis of the optical system makes a cyclic spiral movement over an extended field of view, in a seeking and target acquisition mode, is then precessed towards a detected target, the nutation amplitude, in a pre-phase mode, being made equal to the target deviation, and, eventually, in a target-tracking mode, makes a circling movement within a limited area in the field of view containing the target.

Abstract: An inertial sensor unit for determining north, has a housing and a positioning gimbal rotatably mounted in this housing about a substantially vertical axis. A releasable, cooperating detent mechanism defines three fixed angular detent positions of the positioning gimbal about the substantially vertical axis relative to the housing. The positioning gimbal is successively rotated into the three detent positions. A fiber optical gyro is mounted on the positioning gimbal. The input axis forms an acute angle with a substantially horizontal axis orthogonal to the above mentioned substantially vertical axis. A signal processing system is provided, to which the signals generated by the fiber optical gyro in the three detent positions are applied. The signal processing system provides, therefrom, the angle between a reference direction and north.

Abstract: For monitoring flight safety of aircraft, a monitoring device accommodated in a pod is provided. The monitoring device has a monitoring unit to be attached to an aircraft. Sensors for measuring aircraft data independently of the sensors of the aircraft itself are provided in the monitoring unit. There is a device for automatically monitoring the operation of the technical equipment of the monitoring unit. In addition, the monitoring unit contains a system for automatically monitoring the pilot's reactions on the basis of aircraft data provided by the independent sensors. Furthermore, the monitoring unit contains a device which responds to deviations of the aircraft from the range of safe flight states. This device triggers an alarm. There is a device responding to the aircraft inadmissibly approaching ground and a collision warning device, which responds to the risk of collision with other aircraft. Also these devices trigger an alarm in the case of danger.

Abstract: In a seeker head a field of view is scanned cyclically for providing picture informations referenced to a seeker-fixed coordinate system. The seeker carries a gyro assembly, which provides attitude variation signals as a function of attitude variations of the seeker relative to inertial space. The attitude variation signals are applied to a coordinate transformer which transforms all picture informations with their addresses into an inertial coordinate system which coincided with the seeker-fixed coordinate system after the completion of the preceding scan. Thereby during each scan all picture informations are transformed into one single inertial coordinate system. After the completion of the scan, the picture informations are again transformed into an inertial coordinate system, which coincided with the seeker-fixed coordinate system at the end of said scan, and are stored in a memory. This is the same coordinate system into which the picture informations will be transformed during the next-following scan.

Abstract: A dome subassembly (10) for missiles consists of a dome (12) and a holding ring (14) connected thereto, The dome (12) is made of sapphire. The holding ring (14) is made of oxide ceramics reinforced by fibre or whisker. Dome (12) and holding ring (14) are connected to each other by brazing. Two brazing methods are indicated.

Abstract: In a steering loop for missiles which are guided to a target by means of a seeker head, the seeker head having a limited field of view, the seeker head determines the line of sight to the target by look angles with respect to missile-fixed pitch and yaw axes. A signal processing computer receives the seeker head signals and generates signals which determine the motion of the missile. These signals are applied to a steering system and guide the missile to the target. In order to avoid loss of the target due to limitations of the field of view of the seeker head, the signal processing computer influences the signals determining the motion of the missile such as to ensure a motion of the missile which holds the line of sight always within the field of view.

Abstract: A scene simulator for generating picture information in real time for testing picture resolving sensors, in particular for testing infrared sensors in target tracking seeker heads, comprises a micro-mechanical mirror array, which consists of a two-dimensional array of mirror elements, which are arranged to be moved between first and second operative positions in response to actuating signals. An illuminating device is arranged to uniformly illuminate the mirror array. The light of the illuminating device, in the first operative position of a mirror element, is reflected to pass by a sensor to be tested and, in the second operative position of the mirror element is reflected into the path of rays of the sensor. A picture computer and driver electronic serve to move the mirror elements into the first or second operative positions such that the sensor to be tested observes a simulated object scene.

Abstract: With push button operated switches having at least one movable and one stationary contact carrier, problems may occur when the push button is not actuated properly and centrally. This problem is overcome by a switch having corresponding annular contacts and concentric guide means.

Abstract: The interface arrangement is provided for data transfer between a carrier aircraft and a missile which is to be launched from the carrier aircraft and which includes a target seeking head. The missile is connected to the carrier aircraft through a connecting cable which contains a small number of wires sufficient for transferring analog data and which is detachable upon launch. For selectively operating the carrier aircraft in conjunction with a missile which is equipped with either (i) a target seeking head producing analog target deviation data or (ii) a image processing target seeking head, at least two interfaces are connected to the connecting cable. One of the interfaces is designed for data transfer via the connecting cable to and from the target seeking head producing analog target deviation data. An other one of the interfaces is designed for data transfer via the connecting cable to and from a image processing target seeking head.

Abstract: A picture detecting sensor unit has a passive sensor resolving a field of view into picture elements having different brightness. Picture processing means receive data from the picture detecting sensor. An additional active LADAR sensor having a laser emitting a laser beam and a scanning system for scanning an area of the field of view by this laser beam provides distance signals from the radiation reflected by an object in the field of view. The scanning of the field of view by the LADAR sensor is controlled by the picture processing means associated with the passive sensor such that the scanning effected by the LADAR sensor is limited to objects detected by the passive sensor in the field of view. A common imaging optical system is provided for the LADAR sensor and the passive sensor. A beam splitter separates the beams detected by the passive sensor and the returning beams of the LADAR sensor.

Abstract: A passive, picture-resolving detector assembly has a matrix detector (32) and an imaging optical device (16,30) for forming an image of an object scene on the matrix detector. The matrix detector includes a two-dimensional array of detector elements (50) and each of the detector elements (50) is arranged to receive, in cyclic succession, a plurality of picture elements of the image in order to improve resolution. A micro-mechanical mirror array (18) having a two-dimensional array of mirror elements (48) is provided and each of the mirror elements (48) is arranged to be alternatively moved, by control signals applied thereto, into a first operative position or into a second operative position. The imaging optical device comprises a first imaging optical system (16) having a beam axis and arranged to form a high-resolution image of the object scene on the micro-mechanical mirror array (18).