Abstract: A laser scanning device for fastest possible deflection or sweep velocities s constructed for use in a laser guide or pilot beam system. The scanning device has two symmetric scanning cylinders which each are caused to rotate about their respective rotational axis or axis of symmetry by a gas stream so as to achieve a rapid beam deflection. Due to the low structural weight and small dimensions of the scanning cylinders with their respective scanning mirrors passing through the scanning cylinder at a slant, angular velocities up to the breaking limit of the material can be achieved.

Abstract: A plurality of electrical conductors or cables are held in place by a cirar member, such as a ring or disk, or by two ring or disk elements forming a pair, to form a conductor or cable bunch. For this purpose a plurality of recesses are provided in the circumferential zone of the ring or disk, for holding a conductor or cable in place in each recess. The recesses in the ring or disk are closed by a rim section. The ring or disk elements have recess forming fingers or pieces which can be rotated into preliminary and final positions with an increased clamping force in the final position. In all embodiments the cable or conductors are held in place by a proper biasing force. The costs for forming cable or conductor bunches and for their final installation have been substantially reduced.

Abstract: A connecting device has at least one bolt and a loop of unidirectional fis bound by or embedded in a synthetic matrix material looping around the bolt to form a looping range extending around the bolt. The resistance of the matrix material in the looping range against squeeze-out is improved by reinforcing fiber layers located in the looping range of the loop around the bolt. The fibers of these reinforcing layers are also bound by the matrix of the synthetic material. The reinforcing fibers form insert and/or cover layers having at least one main fiber orientation which extends at least approximately in the direction of the longitudinal bolt axis whereas the unidirectional fibers forming the loop extend approximately tangentially to the bolt in the looping range.

Abstract: The tail end structure of an aircraft has a cross-sectional configuration th laterally and downwardly extending lobes reaching outside a circular cross-section tail end structure, yet staying within the silhouette of the circular cross-section tail end structure as viewed from the top, the side, and the bottom, whereby the boundary layer formation and the boundary layer separation are improved as compared to a tail end structure having the circular cross-section.

Abstract: Information regarding an object, especially brightness information, is obned by scanning the object with an optical scanner, especially an infrared scanner to provide a respective analog signal. The analog signal is produced by passing the received radiation past a chopper disk onto a detector through a secondary optical assembly. The output signal of the detector is digitized and supplied to a fast Fourier transformation processor which also receives a counting signal derived from the oscillation of the chopper disk. The system may be used, for example, for obtaining deviation and/or presence signals regarding the orientation of an earth satellite relative to the center of the earth.

Abstract: A system for setting or driving wedge sockets into holes of a structural ponent combines a mounting member having two shaft sections forming the socket, with a driver having a pistol shape with a pistol grip and a trigger for releasing an automatic impact force. The driver, for example energized by compressed air or by a cocked spring, applies a predetermined impact energy to one of the two shaft sections. The apparatus enables an operator to work efficiently, especially where large numbers of such fasteners must be set.

Abstract: A weapon control for a droppable weapon such as a bomb, has at least two sors for producing impact related or environment related signals for a microcomputer forming part of the weapon. The microcomputer evaluates the signals received from the sensors for producing different control signals for different situations as signified by the sensor produced signals. If the weapon has hit a hard target surface the responsive control signal detonates the weapon instantly. If the weapon got stuck in a soft target, the weapon is placed into a lurking state for a later detonation or defusing.

Abstract: A disk wheel, especially a railroad wheel, has a composite construction of single piece metal hub and a single piece metal rim connected to each other by a wheel disk of fiber reinforced composite material providing exclusively adhesive bonds. The wheel disk transmits shearing stress between hub and rim. The rim is provided with two radially inwardly extending rim flanges. The hub has two radially outwardly extending hub flanges. The shearing stress transmitting wheel disk (12) has a radially outer rim contacting surface (9) adhesively bonded to the rim (3) and rim flanges (7), and a radially inner hub contacting surface (8) adhesively bonded to the hub (2) and hub flanges (6). The wheel disk (12) is inserted into the space between the concentrically arranged hub and rim as long as the composite material is not yet cured and hence sufficiently deformable. The wheel disk is exposed to compression during curing.

Abstract: A liquid crystal light modulator is constructed for the transmission of sch signals modulated onto a light carrier passing through gaseous, liquid, and solid media such as air, water, or glass. A large surface area modulation of the light is accomplished in the visible and infrared range over narrow, however adjustable, wave length ranges or widths. Several circuit arrangements for such modulators are disclosed and their function described.

Abstract: A detonator safety device for a weapon, such as an artillery shell or a war ead, includes a detonator member, a detonator charge and an igniter plate for applying a firing impact with the aid of the igniter plate on a main explosive charge of the weapon in response to the firing of the detonator charge by the detonator member when the device is in a firing position. The arrangement is such, that the main explosive charge cannot be fired by the igniter plate when the device is in a safety position even if the detonator charge should accidentally be fired.

Abstract: A wheel set for rails has a divided axle and two wheels rigidly attached to he respective axle section. The axle sections are interconnected in a force transmitting manner by a clutch for adjusting a differential r.p.m. between the two axle sections. However, the clutch components also permit a relative rotation when the clutch is not energized. The clutch has an inner clutch component and an outer clutch component forming a work gap (7.4) between the clutch components. The work gap extends concentrically to the rotational axis of the shaft and is filled with a magnetizable powder for engaging and disengaging the clutch components which are so mounted to the respective axle section that an axial displacement of the clutch components relative to each other is prevented.

Abstract: A rotor for a rotary wing aircraft has two damping structures on the outs of the blade angle adjustment sleeve. Each damping structure is a sandwich of an elastomeric layer between two stiff cover layers. A two-armed strut passes through the blade neck and is connected at its center in a pivoting manner to the blade root. The threaded outer ends of the two-armed struts pass through the respective sandwich for yieldingly connecting the radially inner end of the blade angle adjustment sleeve to the blade root. By tightening nuts on the threaded strut arms the elastomeric layer may be compressed. Thus, the damping structure performs, in addition to the damping function, a connecting function for the blade angle adjustment sleeve.

Abstract: A rotor, especially for rotary wing aircraft, has a rotor hub (1) with one r more torsionally stiff rotor hub arms (1.1) projecting radially outwardly. A rotor blade (2) having a blade root (2.1), a blade wing section (2.3), and a torsionally flexible blade neck (2.2) is attached by bolts (3) to each rotor hub arm (1.1). A torsionally rigid blade angle control sleeve (5) extends without contact along each blade neck (2.2) and is rigidly connected at its radially outer end to the blade wing section (2.3) and is movably connected at the radially inner end to the blade root (2.1). In order to isolate the blade control from any blade flapping movements, and to reduce the distance between the flapping hinge point and the rotor hub (1), the rotor hub arm (1.1) is flat in a direction perpendicular to the blade rotation plane and is more flexible to blade flapping movements than the blade neck (2.2) is. The blade root (2.1) is in the form of a yoke or fork for attachment to the rotor hub arm (1.

Abstract: A geostationary sun oriented communications satellite has an operational module with a payload platform rotating at one r.p. day. The antenna components are mounted on the platform. The antenna components are so oriented relative to each other and to the platform that an efficient folding and unfolding is possible without any complicated mechanism.

Abstract: A guide beam and tracking system for acquiring a target and for guiding a ying body into the target operates in accordance with the beam rider principle. A tracking laser beam is imaged into the path of a guide laser beam so that both beams travel through the same optical devices and through the same deflection device. All components of the system, except the receiver are controlled by a central processing unit which may control one, two, or three laser generators to produce, in timed sequence, laser beams for different purposes. A highly precise target acquisition and a precise target tracking is achieved.

Abstract: The attitude of a satellite in an earth orbit is determined by a measuring arrangement which includes the body (1) of the satellite oriented with regard to the sun and a functional component (2) rotationally connected to the satellite body (1). The functional component 2, such as a turntable, carries functional elements, for example, antennas, which are directed or oriented toward the earth. During an earth orbit of the satellite, the turntable (2) carries out one full revolution in the direction of the earth orbit about a rotation axis (3) perpendicular to the orbit plane. A first star sensor (4) is arranged to sight in a direction along the rotation axis (3). In order to achieve a high attitude accuracy in the orientation of the turntable (2), the first star sensor (4) is mounted on the turntable(2) and at least one second star sensor (5) is also mounted on the turntable but with a sight direction (6) deviating from the direction of the rotation axis (3).

Abstract: A system for manned or unmanned flying bodies detects covered or hidden targets on the ground by using relatively "longwave" radar radiation for immediately attacking such ground targets, which may be covered by trees for example, but located on a strip of ground extending with a given width below the flight path of the flying body travelling in low altitude flight. Four radar receiver antennas are equally spaced from each other along the wings of the flying body and one transmitter antenna is located between two pairs of receiver antennas. The receiver signals are submitted by a fast Fourier transformation for providing a wavefront reconstruction. The so transformed, received signals are then evaluated in accordance with the known SAR principle directly as the signals are received and transformed by correlation with expected signal functions, so-called reference function, for producing a control signal for the direct or indirect discharge of a weapon.

Abstract: The flight path of a flying body, such as an artillery shell, is stabilized gainst disturbing forces and against pendulum type motions by fluid steering jets ejected from said flying body for causing forces countering the disturbing forces. The steering jets pass through a fluid jet distributing member which has inlet openings communicating with fluid ducts leading to a fluid supply chamber. The distributing member is mounted in the flying body by a spring which permits a deflection or shifting of the distributing member in a direction across a central longitudinal axis of the body.

Abstract: An aircraft wing is equipped with at least one low compression fan which blows into a longitudinal flow channel extending lengthwise or spanwise of the wing and leading into air blowing nozzle arranged along the upper wing surface where the reduced pressure is largest for directly mixing the propulsion air jet or jets with the boundary layer air flowing along and adjacent to the upper wing surface. Both, the flow channel and the air blowing nozzles extend substantially along the entire length of the wing for increasing the resulting propulsion force and/or the resulting lift due to the mixing of the propulsion air jet with the boundary layer air directly in the boundary layer.

Abstract: A guide beam and tracking system for steering a flying body toward a target n accordance with the beam rider principle, is constructed for use under adverse weather conditions. Even under such adverse weather conditions a highly accurate target acquisition is assured due to the use of optical conversion, and beam expansion in the transmitter path, and heterodyning in the laser receiver. It is thus possible to achieve in addition to the highly accurate target acquisition, an accurate tracking of a flying body moving toward a target, under the control of a guide beam device.