Abstract: The invention is directed to a hollow or projectile charge with an explos material charge (6) and a lining (9) acted upon by the detonation of the explosive material and forming a spike or a projectile (16). In order to achieve the highest possible accelerations for the spike or projectile, the lining (9) is constructed as a part of the hollow space (10) with walls (4, 5) of a good electrically conducting material in which a primarily fed magnetic field (H) is enclosed and compressed by means of the detonation of the explosive material (6). The hollow space (10) is preferably formed by means of a coaxial system (3) of an inner conductor (4) and an outer conductor (5), which coaxial system is short-circuited at both sides, wherein the outer conductor is encased by explosive material (6). During the detonation of the explosive material, the outer conductor (5) is pressed against the inner conductor so that the hollow space (10) located between the outer and inner conductor is constantly reduced.

Abstract: In an arrangement for combatting ground targets by a projectile launched m a flying weapons carrier, a launching device is located in the weapons carrier for directing the projectile in a downward and rearwardly inclined direction relative to the flight direction of the weapons carrier. An aiming system connected to control units adjusts the horizontal velocity of the weapons carrier to the same magnitude as the oppositely directed ejection velocity of the projectile. The projectile can be released in the nadir above the target.

Abstract: A control system having a main loop comprising a deadband section having iable thresholds. An adaptive network derives from a deviation signal, in one or more selected frequency ranges, by averaging, an adaptive signal which when injected into the deadband section allows its thresholds to be continuously or discretely adjusted in accordance with a desired function to increase the accuracy and reduce the corrective energy consumption of the control system.

Abstract: A vibration isolator is formed with a spring mechanism and a fluid transmion mechanism interposed between a vibrating member and a support member. The fluid transmission mechanism includes a primary fluid chamber and a secondary fluid chamber, with the secondary fluid chamber being deformed to a greater extent than the primary fluid chamber as a result of vibrations. An inertia mass operatively associated with the secondary fluid chamber is displaced as a result of vibrations and is thereby accelerated with a resulting inertia force causing fluid pressure change in the fluid transmission mechanism which compensates as a dynamic force the dynamic portion of the spring force transmitted from the spring mechanism to the support member.

Abstract: A device for use on aircraft or spacecraft provides data corresponding to the course and orientation of the craft, and a digital display of the terrain over which the craft is travelling. The device includes at least first, second and third sensor lines consisting of parallel rows of photosensitive semiconductor elements arranged transversely of the flight path of the craft. The sensor lines provide line images corresponding to terrain images directed onto the lines, and the lines are spaced apart from each other so that a first terrain image sensed by the lines during a first scanning period partially overlaps a second terrain image sensed by the lines during a second, successive scanning period.

Abstract: The invention is directed to a method for determining the anomaly portion the output signal of a zero-seeking earth-horizon sensor for a geostationary satellite. The horizon sensor comprises a chopper disk operated with constant frequency, which chopper disk pictures the image of oppositely located earth horizons on a common infrared detector. When the thermal radiation of the two earth horizons is different the anomaly portion contained in the detector output signal can be determined in that the off-course signals are measured for different amplitudes of the chopper disk. Since the anomaly-dependent portion in the detector output signal depends on this chopper amplitude, correcting amounts can be determined for the measured values corresponding to the anomaly portion.

Abstract: A method and apparatus for deriving an off-course signal for an orbiting th satellite, preferably a geostationary satellite, by an earth-horizon sensor. The earth-horizon sensor operates in the infrared range and comprises, in the focal plane of an input lens, a chopper disk, which is periodically reciprocated with a determined chopper frequency (f) and which has a diameter corresponding to the image of the earth, and a detector (1) receiving the periodically interrupted radiation of opposite earth rims. The output signal of the detector is demodulated synchronously with the chopper frequency (f) and corrected with a correction signal corresponding to different temperatures of opposite earth rims (earth anomaly).

Abstract: A method and a circuit for processing the signals of an earth-horizon sen of a circularly orbiting earth satellite. The earth-horizon sensor operates in the infrared range and includes, in the focal plane of an input lens, a chopper disk which is periodically reciprocated with a determined chopper frequency (f) and has a diameter corresponding to the image of the earth, as well as a detector (1) receiving the periodically interrupted light radiation of oppositely located earth rims. The output signal of the detector (1) is demodulated synchronously with the chopper frequency (f) in order to derive an off-course signal. In order to suppress the influence of the earth anomaly, the amplified output signal of the detector (1) is additionally synchronously demodulated with the doubled chopper frequency (2f), according to the invention, in order to produce a symmetry signal.

Abstract: An airfoil particularly suited for use in rotor blades of large wind-driven ower plants is formed in three modular sections including a nose or leading section, a spar section and a trailing section, each separately formed and subsequently assembled. In the method of the invention the spar section is formed in two separate mold units which are configured to form part of the upper and lower aerodynamic profile of the airfoil and the two spar section units are trimmed along a junction plane and then joined together at the junction plane to form the spar section of the airfoil.

Abstract: An arrangement for the attitude stabilization of flexible vehicles, such as ircraft and spacecraft. Such vehicles, due to their lightweight construction and/or large spatial extension or high degree of slenderness, have structurally weakly-dampened bending vibrations and/or torsional vibrations. For generating the forces and moments required for stabilizing such vehicle, discontinuously operating units are used. In one embodiment, for each vehicle axis, an observer or Kalman filter is employed for obtaining estimated values of the state variables of the vehicle system to be controlled. The observer has a first transfer function of at most third order. A state controller device is responsive to the observer for controlling the state variables. A modulator network is responsive to the state controller device wherein the modulator network has a relay characteristic.

Abstract: In the disclosed satellite and arrangement therefor, roll or yaw of a satite with pitch momentum bias and travelling on a substantially polar orbit with the aid of a coil interacting with the earth's magnetic surface includes a timing arrangement for dividing the orbit of the satellite into four successive quadrants P1, P2, P3, and P4, with the quadrants being inclined at an angle of 45.degree. to the equator and the quadrants P2 and P4 being polar quadrants and the quadrants P1 and P3 being equatorial quadrants. A first control unit produces satellite control signals in response to the timing means which are arranged to use the first control while the satellite is in the polar quadrants and the second control unit when the satellite is in the equatorial quadrants. The sign of the control unit is inverted in the quadrants P3 and P4, but maintained in the quadrants P1 and P2. Both controls use or generate internal signals corresponding to the roll angles and roll velocity to produce the control unit signals.

Abstract: A sensor device of the type to be carried on aircraft or spacecraft which avel along an arbitrary flight path, operates to provide data corresponding to the course and orientation of the craft, and a digital display of the terrain over which the craft is traveling. The device includes at least first, second and third sensor lines comprising rows of photosensitive semiconductor elements, arranged transversely of the flight path in an image plane. Each of the sensor lines provides line images corresponding to a terrain image projected onto the sensor line. At least one of the sensor lines extends in the image plane to form angles relative to the other sensor lines, so that the terrain line images produced by the angled sensor line intersect the terrain line images produced by the other sensor lines. This arrangement results in establishing clearly defined connecting points of the images, and provides high accuracy in the determination of the orientation data and of the terrain.

Abstract: In a low-flying weapons carrier, such as a manned or remote control aircr, a weapon is arranged to fire steeply downwardly at ground targets. The weapon can fire a plurality of separate ammunition members. A release for the weapon is located in the weapons carrier and a target detector separate from the weapon is associated with the release. The target detector is directed steeply downwardly parallel to the velocity vector of the ammunition members to be discharged by the weapon.

Abstract: A safety steering column assembly for automobiles, arranged to shorten under the effect of a predetermined force exerted during an impact accident, includes a steering column with a safety sleeve forming a part of the column. The safety sleeve is a grid tube made up of wound laterally spaced grid strands. Each grid strand consists of a plurality of plastics material impregnated fiber strands. The grid strands are located outwardly from and are wound angularly of and around the steering column axis. Adjacent grid strands having the same angular orientation relative to the axis are spaced laterally apart. Further, the grid strands are disposed in crossing relationship.

Abstract: A method of aligning an aircraft fuselage axis with an air or ground targ while maintaining a predetermined flight path, involves turning the fuselage around the yaw axis and the transverse axis relative to the flight path. In performing the fuselage turn a side-slip angle is effected by vertical rudder control and superposed thereon is an oppositely directed roll angle. The actuation of the flight control for the fuselage turn is coupled with the fire control system of the aircraft.

Abstract: A suspension system for rail vehicles which have at least two wheelsets hng axles which are supported in a frame and within which a cross member extends parallel to the axles. The cross member is supported in the vehicle frame in a spring-cushioned manner wherein the frame with the integrated cross member consists essentially of an H-shaped part made of resiliently elastic fiber-reinforced material.

Abstract: An accelerating grid particularly for an ion beam, consisting of at least e orifice plate which is fastened along an elastic outer rim thereof to a support. The orifice plate or plates includes a plurality of through-holes with mutually oriented central axes, preferably directed towards a common focusing point. A plurality of slots in the elastic outer rim maintain the alignment of the orifice plate center relative to the focus point during heat-induced expansion of the plate.

Abstract: Ammunition for combatting armored targets includes a flying body with an act end and a trailing end. A penetrating warhead is located within the flying body spaced from the impact end. Between the impact end and the warhead, a projectile in the form of a plate of inert material is provided. The surface of the plate facing the warhead is covered with an explosive charge. When the flying body impacts against a target, first the plate-shaped projectile forms an opening through the target sufficient for the warhead to pass through the opening to the interior of the target.

Abstract: In a guided missile, in which an altitude-sensing control causes the miss to descend to a predetermined constant low altitude at a specified time before reaching a target ship, a timing mechanism waits for elapse of a predetermined interval from the descent and only then allows passage of a signal, indicative of the missile flying over a target from the control, to a warhead-detonating fuze.

Abstract: A two-dimensional, unidirectional oblique air impact diffuser is used as an air inlet for a gas turbine jet engine for aircraft. The air inlet includes an upper rigid air inlet ramp and an air inlet bottom spaced below the ramp. An air scoop lip is pivotally attached to the air inlet bottom so that it can be pivoted from a standard setting point downwardly away from the air inlet ramp and also from the standard setting point toward the ramp. The pivotal displacement of the air scoop lip is a function of the aircraft angle of attack and the flight Mach number. The angular displacement of the air scoop lip from the standard setting point increases downwardly as the aircraft angle of attack increases and decreases as the Mach number increases.