Abstract: A connector for coupling a medical laser tool to a laser has a housing with coupling fitting at one end which is plugged into a laser receptacle and with a light conductor cable connection at the other end. The light conductor cable in turn is connected to the laser tool. The coupling fitting includes, in addition to the optical coupling element, heavy and light duty electrical contact members for an electrical power and data transmission and a gas conduit coupling for a gas transmission through the connector.

Abstract: The conditions for detonating a follow-up charge in a dual stage weapon are etected for detonating the follow-up charge either instantaneously or after a time delay. An instantaneous detonation is caused when the dual stage weapon should not penetrate sufficiently through a target surface or when the weapon rebounds. A delayed detonation is intended when the dual stage weapon has penetrated a target. The delayed detonation shall be responsive, preferably randomly, to an approach to the weapon. This type of control of the weapon detonation in response to different detonating conditions is accomplished by using two, preferably three acceleration or vibration sensors producing signals which are evaluated for determining the respective detonating condition.

Abstract: A food supply system is adapted for installation in an aircraft having an upper and a lower deck. A pantry is located on the upper deck. A food supply carts carrying platform is arranged on the lower deck for cooperation with the pantry on the upper deck. A lifting mechanism is arranged for cooperation with the platform for lifting or lowering selectively any one of a plurality of food supply carts whereby the space requirements on each deck are optimally reduced.

Abstract: A gyroscope with a rotor which rotates about a nonrotating axis is simple its structure and has but a few movable parts because the rotor axis (2) is divided into two sections by an articulation piece (8), whereby one section (2a) is connected with the housing (11) and the other section (2b) is tiltable about the articulation piece and carries the bearing axis (13) for the rotor (5). The articulation piece (8) is arranged approximately in the center of gravity of the rotor (5). The gyroscope (10) may be constructed to have one or two degrees of freedom and it may be equipped with the measuring device necessary for its operation as a displacement gyroscope or as a rate gyroscope. For a measuring operation in which the rotor (5) is driven only for the uptake, a compensating circuit is provided with an amplifier (23), a servo-control (24), and a multiplier (25) for producing a measured signal proporational to the measured quantity independently of the r.p.m. of the rotor (5).

Abstract: Structures subject to a high operational stress, such as weapon launchers, ombustion chambers, artillery barrels and the like, are strengthened dynamically by a counter-pressure generated simultaneously with the load causing the operational stress. The counter-pressure causes a dynamic stress which is effective temporarily to counteract the operational stress. In a weapons launcher, for example, the operational stress occurs in a launching tubular member and the counteracting stress occurs simultaneously in a second tubular member surrounding the first launching tubular member.

Abstract: An antenna reflector, for example for a satellite or spacecraft, has ribs urnalled to a central body by a first journal axis. Each rib has a radially inner section tiltable and lockable relative to the central body, and a radially outer section journalled to the inner rib section at a second journal axis for tilting and locking the outer rib section relative to the inner rib section. A motor driven cable drive and respective pulleys are so arranged that the inner rib sections are first partially unfolded before the outer rib sections begin to be unfolded. The outer rib sections then are moved faster than the inner rib sections so that both rib sections reach the fully unfolded state substantially simultaneously. The folding takes place in the reverse order, whereby the outer rib sections are folded first. The reflector netting is stretched out only after the ribs have been locked into the unfolded state.

Abstract: Aerodynamic flow conditions at the air intake of gas turbine engines, espally aircraft engines, comprising boundary layer deflectors are improved by movably arranging the boundary layer deflectors so that they may be retracted flush into the aircraft fuselage during take-off and low speed flight, and may be extended to an operating position during high speed flight. A similar retractable boundary layer deflector may be provided for an air intake for an auxiliary engine, which operates intermittently to drive auxiliary devices of an aircraft. When the auxiliary engine operates the air intake is open and the deflector is extended thereby improving the intake air flow conditions. When the auxiliary engine is shut down, the air intake is covered by a control flap and the deflector is retracted flush into the fuselage.

Abstract: A block type electrical terminal connector, especially for use in aircraft nd spacecraft, has a pot-shaped housing of electrically insulating material permanently closed at its bottom and closable at its open top by a cover. A single piece contact bank for connecting groups of contact pins together, that is to the same potential, is made of a band of sheet metal, so that contact elements, contact pin retainers and arresting members form integral components of the single piece contact bank which is inserted into the open top of the housing and held in the housing by the cooperation of locking shoulders in the housing with the arresting members of the single piece contact bank, whereby the contact bank is retained in the housing even without the cover closing the housing. This construction substantially reduces the number of connector parts and simplifies the structure and assembly of the connector.

Abstract: The steering of a jet propelled flying body is improved by positioning jet eflector flaps into the propulsion jet for deflecting the propulsion jet. The deflector flaps can steer the flying body automatically in response to a flight control unit either alone or as a support steering system for the control surfaces of the flying body. The jet deflector flaps are arranged in the jet nozzle in a cross or star configuration and preferably near the periphery of the jet nozzle.

Abstract: Work piece surfaces are peened by electromagetically controlled steel nees which are guided for back and forth sliding movement in a guide plate. Each needle has its own electrically controllable drive magnet. All the magnets are energized in a controlled sequence by a control unit which energizes the drive magnets in a given sequence or pattern and in accordance with adjustable parameters such as the stroke amplitude and frequency of each needle stroke. Thus, the work piece may be deformed into a particular shape and/or its surface may be work hardened or densified and areas of different surface stress may be produced in the work piece surface. Work pieces may be shaped into any desired three-dimensional curvature.

Abstract: An umbrella type unfoldable antenna reflector net is supported by carrier bs extending radially from a carrier body and by auxiliary ribs extending between adjacent carrier ribs. Bracing wires are connected between the carrier ribs and the auxiliary ribs. The tension of the bracing wires, which in the unfolded state of the reflector net extend substantially in the direction of chords, is adjustable by respective adjustment members so that the bracing tension force has a force component which extends substantially perpendicularly to a plane defined by the unfolded reflector net. The adjustment members permit adjusting the reflector net into a parabolic shape.

Abstract: A diffuser for an air intake of an aircraft has an inlet and an outlet, both with variable cross-sectional flow areas. At least one wall section of a diffuser defining flow channel is movable by one or separate lever linkage systems for varying the inlet and outlet cross-sectional flow areas. A control circuit, preferably a closed loop control circuit responsive to a control program, makes sure that optimal flow cross-sectional areas are maintained at the inlet and outlet of the diffuser to optimize the operation of the diffuser.

Abstract: An acceleration sensor comprises a housing formed with a hollow cavity deing a sensing direction. An acceleration sensing conductive mass is releasably mounted in the cavity. The mass is released by a cutting member which severs the releasable mounting of the acceleration sensing mass. A force applying assembly is activated to cause movement of the cutting member. Switch electrodes are arranged at the lower end of the housing cavity. The mass falls through a predetermined distance and bridges the switch electrodes. The sensing mass, when severed, may move in incremental steps due to the use of a two-stage releasing assembly. Sensing transducers may be located along the falling path of the acceleration sensing conductive mass.

Abstract: A structural component having a curved wall, such as an aircraft fuselage pipe, has a grid structure formed of box frames produced by winding tapes of fiber reinforced synthetic material, so-called prepregs, onto mold bodies. These mold bodies are then assembled on a mandrel for covering with a planking and curing whereby the tapes are bonded together to form stringers intersecting with ribs in a grid structure and whereby the planking is bonded to the grid structure. The ribs are reinforced by fiber reinforced belt segments of synthetic material inserted into gaps between adjacent short ends of the mold bodies, whereby these belt segments are bonded to the ribs during curing. The belt segments have a width corresponding to a multiple of the width of the stringers and hence protrude radially inwardly. Preferably, an edge reinforcing strip of fiber reinforced material is arranged alongside the radially inner edge of the belt segments.

Abstract: A vibration isolator (1) with two degrees of freedom works according to the nti-resonance principle. The vibration isolator is arranged, for example, between a first body, such as a helicopter frame 13, and a second vibration generating body such as a rotor-transmission unit 12 vibrating at a predominant frequency. A spring arrangement (2) is connected to the attachment points (14, 15) for the first and second bodies. The spring arrangement works in conjunction with a pendulum rod (3) which is attached to the two bodies (12, 13) by spherical pivot bearings (5, 10). The vibration isolator has a compact construction and a low characteristic damping since the spring arrangement includes several relatively small semi-circular or spiral-shaped wound leaf springs (7-1 to 7-4) which extend between an inner ring (4) and an outer ring (6). The pendulum rod is held in a spherical pivot bearing (5) in the inner ring, and a further spherical pivot bearing (10) is connected by a flange (9) to the outer ring.

Abstract: The invention relates to a method and an arrangement for the wings of a h speed aircraft, for increasing the flutter velocity. Aerodynamic auxiliary flaps or vortex generators are placed into an effective position in response to filtered sensor signals for causing a reduction in the local lift rise or for shifting the local neutral point toward the wing trailing edge to thereby provide an effective "flutter brake". The auxiliary flaps or vortex generators are activated only once when needed and stay in an activated effective position for a length of time sufficient for increasing the flutter velocity or speed and the activation takes place rapidly in about 200 to 400 milliseconds from the time the sensors pick up or provide a signal for such activation.

Abstract: Magnetic field distortions are sensed by a magnetic sensor including a magnetic field sensor or receiver arranged for cooperation with a magnetic transmitter which generates the magnetic field for providing measured values representing such distortions. The magnetic receiver has a preferred directional axis in which the receiver is sensitive. The receiver is so arranged or located that the undistorted magnetic field lines of the magnetic field produced by the magnetic transmitter extend approximately perpendicularly to the preferred directional axis of the magnetic receiver. By locating the receiver in this specific position it is possible to substantially increase the sensitivity of such sensors and hence their sensing range for example in measuring the spacing between a magnetically levitated vehicle and a rail surface relative to which the vehicle is travelling.

Abstract: Structures subject to a high operational stress, such as weapon launchers, ombustion chambers, artillery barrels and the like, are strengthened dynamically by a counter-pressure generated simultaneously with the load causing the operational stress. The counter-pressure causes a dynamic stress which is effective temporarily to counteract the operational stress. In a weapons launcher, for example, the operational stress occurs in a launching tubular member and the counteracting stress occurs simultaneously in a second tubular member surrounding the first launching tubular member.

Abstract: Control force errors are automatically eliminated in aircraft, especially licopters. Such errors may occur because of disturbing forces that act on a control stick (1) for the elevator and/or rotor blade adjustment. The following features are combined. A main control drive (3) for the adjusting of the elevators and/or rotor blades is connected through a control linkage (2) with the control stick (1). A spring box (5) with a pretensioned spring (17) is connected through a control rod (14) to the control stick (2) and to one end of the spring box (5). A trimming rod (15) of a trimming motor (4) is operatively connected to the other end of the spring box (5). To compensate the disturbing forces caused by the inertial mass forces acting upon the control stick (1) as much as possible there are further provided two displacement pickups (6) and (7) or a single displacement difference forming pickup (16). A first summing circuit (8) receives the output signals from the two pickups (6, 7).

Abstract: The control of the longitudinal or pitching stability of aircraft is imprd by providing a corrected control characteristic for the correction adjustment drive which is interposed between the pilot operated control stick and the main control drive, for example for the blade angle adjustment in a helicopter or for the elevator adjustment in fixed wing aircraft. A control linkage (2) is connected on one end to a main control drive (4) for the elevator or rotor blade adjustment and at its other end to the control stick (1). The correction adjustment drive (3) is interposed in the control linkage (2). A displacement pickup (5) measures the control displacement of the control linkage (2) and a flight speed pickup (6) measures the flight speed.