Abstract: A device for locating artillery and sniper fire with a sensor and acoustically triggered marking means. An igniter is provided with the acoustic sensor and is adjustable in terms of frequency and/or pulse pattern. A remover preventer is provided and the components are provided in a shell-proof housing whereby removal triggers the marking means.

Abstract: An apparatus for removing heat from a thermally highly loaded structure, such as a spacecraft or hypersonic aircraft, is based on an endothermic reaction, and particularly the water gas synthesis reaction. A system of pipes (2) is arranged in the areas of the structure that are to be cooled. The pipes (2) are filled with a carbon core that includes passages through which steam passes, to react with the carbon and generate water gas. The system preferably includes a steam generator that uses some of the heat from the areas to be cooled for generating the steam that is conveyed through the carbon filled pipes (2).

Abstract: The invention provides a reflector antenna, especially for a communications satellite, having at least one fixed main reflector (102) with an essentially circular aperture. A fixed feed system (118) includes a horn radiator (108) with a rotationally symmetric radiation diagram and a fixed polarization direction. An auxiliary reflector may be arranged to be rotationally positionable around a main axis (E) and has a reflecting surface that is shaped as a partial surface of a nonrotationally symmetric ellipsoid with a low numerical eccentricity, which illuminates main reflector (102) elliptically with an ellipticity that is essentially constant regardless of the rotational position.

Abstract: A load glider has, between the parachute surface and the load, a device in which a reversible transfer of mechanical energy from the main lines to the steering lines takes place, so that essentially only frictional forces are to be overcome during the operation of the steering lines. The device includes two differential gears, which are arranged in parallel and are accommodated in housings in which a steering line is wound up on a roller with a larger diameter and a main line is wound up on the other roller with a small diameter. Gears, which can be driven by pinions driven by electric motors, are flanged onto the larger rollers.

Abstract: In an energy generating system, which is preferably suitable for satellites and space stations, a total of four Stirling engines are combined together into a cross-shaped unit, in the center of which is arranged a cross-gear drive that is acted upon by the pistons of the Stirling engines. Therein, two planet gears revolve around in internally toothed annular gears. The common shaft of the annular gears is connected with the piston rods of the Stirling engines by an inner crankshaft, which simultaneously carries the planet gears, and by an outer crankshaft articulately connected with the inner crankshaft. Both crankshafts comprise counterweights as balancing masses, whereby a complete mass balancing of the cross-gear drive and therewith a vibration-free operation of the entire arrangement is achieved.

Abstract: The vibration absorbers have mounts for radial fastening of the vibration absorber to an inside surface of a wheel rim to be used on rails. A plurality of mounts are uniformly distributed over the circumference of the inside surface and are each coupleable to the wheel rim in an acoustically good conducting manner against a surface that matches the radius of curvature of the inside surface. On each mount at least one vibration absorber consisting of a sequence, running in the radial direction, of metal and plastic plates can be coupled in an acoustically effective manner by means of a coupling surface. The vibration absorbers and mount are releasably connected with one another and have a coupling surface that is always the same and is independent of the radius of curvature of the inside surface of the wheel rim.

Abstract: A coil form with a coil support and with a winding applied thereto, whose turns are provided with a coil bond material. The bond material contains a volatile solvent and mutually fixes the turns when dried (in a dry state). To guarantee an essentially uniform, nearly solvent residue-free drying of the coil bond in the entire winding even in the case of a very large number of coil layers, the coil support is a porous coil support having open pores. The coil support has a diffusion coefficient with respect to the solvent that is equal to or slightly lower than that of the winding.

Abstract: The invention relates to a device for self-defense of aircraft against missiles and provides for a combination of a proximity sensor for the enemy missile, an intercepting rocket, and an aimed light beam, with the light beam optionally being used alone as an optical jammer against an optical homing head on the missile, or being used together with the intercepting rocket to steer it optically by either a semi-active or a beam rider steering method.

Abstract: Thrust-generating device with rocket engines arranged in pairs opposite each other for multiple ignition as well as individual and group activation and with an amount of fuel sufficient for the duration of the mission. The thrust-generating device is designed as a closed, storable, modular unit. The rocket engines are operated with liquid fuel and liquid oxidizing agent. At least one tank is provided for each fuel component. The tanks are in the filled, pressureless state before the activation of the thrust-generating device. The rocket engines and a fuel distributor of block design are integrated within a central bulkhead. The thrust-generating device is surrounded by a sealed outer jacket and is divided by the bulkhead into two separate chambers. The outer jacket is lined on the inside with a "self-sealing" film. The oxidizing agent is stored in one chamber, and the fuel in the other chamber. The empty spaces in the chambers contain an adsorbent filling.

Abstract: Fuel supply system for multijet airplanes using cryogenic fuel with one tank or one tank group for each engine or for all engines on one side of the longitudinal central plane of the airplane, and, if desired, with an additional, common tank or an additional, common tank group for all engines. A transfer line with shut-off valve leads from each tank/tank group associated with a defined engine or with the engines of one side of the airplane to at least one other tank/tank group and/or, if desired, to the tank/tank group common to all engines. If desired, at least one transfer line leads from the common tank/tank group to at least one other tank/tank group.

Abstract: A fluidic nozzle which is flown through by a singular injection jet and which periodically deflects the injection jet. The nozzle has a nozzle channel, whose cross section is expanded in relation to the injection jet, and with control openings opening into the nozzle channel downstream close to the neck of the nozzle for injecting a control fluid that brings about the deflection of the jet. The nozzle channel has a channel cross section, which is two-dimensionally expanded in height and width in relation to the cross section of the jet, with a cross-section contour corresponding to the desired distribution cross section, and it is provided with a number of control openings. The control openings are arranged offset in relation to one another in the circumferential direction of the nozzle channel and are activated one after another in sequence to generate a jet movement rotating along the circumference of the nozzle channel.

Abstract: The invention relates to an all weather visual system that combines information from a ROSAR type radar sensor with navigation and flight information to provide artificial vision for the pilot. The radar utilizes the movements of rotating arms fixedly mounted on the rotor head of a helicopter. For this purpose, a turnstile is used as the central carrier structure, which is protected by an aerodynamically shaped body against atmospheric forces. The radar transmitter and radar receiver are located on the rotor head and in the tips of the rotating arms, respectively.

Abstract: Laser weapon system whose laser device is a target reconnaissance system with a visual device, rangefinding and exposure measuring devices, and a control computer for adjusting the laser energy, with the laser device being associated with a beam-aiming unit and with the viewer being associated with a monitor as well as an image processing unit provided with a marking and tracking device for the target individuals.

Abstract: The present invention is directed to an optical proximity fuse for missiles with laser transmitters and optical receivers, whose optically bundled beam paths are oriented in such a way at a small angle to the direction of flight that they intersect in predetermined measuring segments, wherein the radiation reflected from objects in these measuring segments is utilized for deriving the firing pulse, wherein at least two laser transmitters oriented at angles different from each other and a common optical receiver are arranged at different points of the front side of the missile. The measuring segments where the transmitter beam paths intersect the receiver beam path lie at different distances from the missile and at differing side spacings from the longitudinal axis of the missile, wherein the measuring segment lying closer to the missile corresponds to the predetermined target segment. The laser transmitters are modulated at identification response codes differing from each other.

Abstract: The arrangement serves to control the structural dynamic response characteristic of a booster rocket, which is provided with a propulsion engine as well as a payload. The booster rocket includes at least one control unit as well as at least one control element for altering a flight path perpendicularly to a lengthwise axis of the rocket. The control element is embodied as a rotatably supported control fin, arranged at a lateral side area of the booster rocket. Sensors are provided to measure lateral wind loads. An adjustment element is connected to the control fin and is adjusted by the control unit in such a manner that measured values provided by the wind sensors are converted into position adjustments of the control fin for compensating crosswise forces.

Abstract: An intercept device for flying objects is formed of a lightweight, small-volume, packable structure made of a tear-resistant, pliable material, which can be stretched to a large, two-dimensional or three-dimensional expansion by means of a deployment device. To reduce the velocity of the intercepted flying objects, activatable, aerodynamic resistance bodies are incorporated into the structure. To end the intercept procedure, elements are integrated into the structure, which consist of material that can be destroyed from outside by means of high-energy beams and/or chemical reagents, or that destroys itself, or the structure as a whole consists of such material.

Abstract: A device with a pyrotechnic gas generator wherein gas pressurizes a hydraulic circuit via a cartridge-case base, a spring and a pressure piston. The pyrotechnic gas generator comprises a propellant charge, which is located in a combustion chamber and is ignited by an electronic igniting unit. The parts of the device are contained in a housing, which is exchangeably inserted into a wall surrounding the hydraulic circuit.

Abstract: In a method for the ejection and distribution of submunition bodies to be ejected from a submunition carrier for combatting targets in a line, such as vehicle columns, the submunition carrier (3) comprises vertical ejecting tubes (3a) for the submunition bodies, which vertical ejecting tubes (3a) are directed downward as well as upward. Submunition bodies (7) which are connected with a wind sock for stabilization are ejected downward. The submunition bodies (9) which are to be ejected in an upward direction are connected with a parachute which is provided with at least one eccentric slot.

Abstract: Fastening of a thermal protection structure on the airframe of a craft such as a spaceplane, rocket, missile, re-entry capsule, or any hypersonic airplane wherein the thermal protection structure consists of a plurality of highly heat-resistant, mechanically stable panels, which may be provided with an additional gap seal if desired, with a plurality of fastening points per panel, which are arranged at spaced locations from one another and establish a positive-locking connection between the insulation structure and the airframe. The fastening has a first fastening point, which does not permit any movement, or it does permit an at least limited rotary movement of the panel around an axis extending at right angles to the airframe surface; a second fastening point, which permits a limited, linear displacement of the panel in parallel to the airframe surface; and at least one additional fastening point, which permits a limited displacement of the panel in all directions.

Abstract: In order to produce lightweight mirror structures or other reflecting components, preformed silicon elements of sufficient wall thickness are applied to a CFC or CMC substrate structure with the dimensions of the component to be produced, at a temperature in the range 1300.degree. C. and 1600.degree. C. either in vacuum or in a protective atmosphere. In this way a mirror structure or reflector is formed directly. It is possible to work at temperatures in the range of 300.degree. C. to 600.degree. C. when the silicon is applied in the form of a preform such as a wafer, which is joined to the substrate by way of a zone of a melt eutectic incorporating a nonferrous metal, which is preferably gold. The surfaces are subsequently coated.