Abstract: A landing gear for loads including cargoes and/or personnel is removably ured to the load. At least one tiltable jet engine forms part of the landing gear and automatically controls the descent movement. A stabilizing mechanism forms part of the landing gear and provides a positioned control for the landing gear and load during descent. Preferably two solid fuel rockets are provided for supporting the load during descent. The rockets are tiltable about an axis extending across the longitudinal axis of the landing gear. The tilting is controlled by a computer on board in accordance with a program present in the computer whereby the landing is substantially independent of local wind conditions and other external factors.

Abstract: The present load lock secures loads, such as containers, or weapons, such bombs, to an aircraft thereby using a single or multiple point suspension system while simultaneously clawing or clamping the load to prevent it from undesired movements. The clawing or clamping is accomplished by the same centrally located mechanism which is operated manually or by an electric drive, whereby operation in one direction results in clawing while operation in the opposite direction results in clamping. In both instances the force causing the clamping or clawing is adjustable as a biasing force. The suspension of the load is accomplished by a power operated hook reaching into an eye of the load. The arming or fuzing of a weapon held in the lock is accomplished by a mechanism arranged laterally in the lock housing for easy access.

Abstract: In a molecular laser a cold gas flow is mixed with the hot gas flow by inducing the cold gas flow through slots (13) arranged upstream of the neck (11) of the Laval nozzle (10) through which the hot gas stream flows. In this way a rapid mixing is accomplished for generating non-balanced conditions in a laser gas. Preferably the mixing takes place substantially in the nozzle neck.

Abstract: This apparatus relates to anchoring self-supporting tall structures such as asts, towers or the like in a foundation. The structure (2) is supported in the foundation (5) at its lower end on a pivot bearing (10). The weight of the tower is borne on this bearing. The structure is furthermore elastically clamped to the wall of the foundation at a location above the pivot bearing by elastic clamping device (11) operatively interposed between the wall of the foundation (5) and the sides of the tower. The clamping device generally comprises spring damper elements for damping and suppressing vibrations. The spacing between the pivot bearing and the elastic clamping device, and the characteristics of the elastic damping material are selected to lower and suppress resonance frequencies in the structure.

Abstract: In a gasdynamic CO.sub.2 laser mixing of hot and cold gasses takes place simultaneously with causing an inversion. The cold gas is air supplied through a compressor at a pressure in the range of 1 to 10 bar into the combustion chamber. Preferably the compressor output is supplied to two points of the combustion chamber, namely a zone directly upstream of and adjacent to the Laval nozzle and a zone in the combustion chamber further removed from the Laval nozzle.

Abstract: The running characteristics of a tire for a wheel are improved to provide a more quiet run, by attaching to an inner and/or outer surface of the tire vibration absorbing elements. Vibration absorbing elements may even be inserted into the tire material itself. The vibration absorbing elements are secured to the tire surface in a force and moment or torque transmitting manner by vulcanization or by a suitable adhesive. A strap may hold the individual absorbing elements together or the elements may form integral parts of the strap which is secured to the tire surface, for example, by a rubber vulcanizing operation. The vibration absorber elements may be secured to an inner tube instead of to the tire.

Abstract: A redundant steering mechanism for a craft, especially an aircraft, comprs redundant control components which become effective when the normal steering components become disabled as a result of an electrical power supply failure. The redundant control components do not affect the normal control system but are effective even if the electrical power supply of the craft should fail. The redundant control components are operated by a hydraulic or pneumatic medium acting as a signal carrier. The control signal is a multicomponent signal, one component of which is derived from the pilot's control stick and other signal components are derived from such factors as the speed, the angle of attack and so forth. These signal components are superimposed to form the mechanical emergency control signal for operating a hydraulic or pneumatic steering element.

Abstract: The noise caused by vehicle tires rolling on a road surface is reduced by enclosing in the space confined by the tire and the wheel rim a noise or sound absorbing or insulating material which may assume various shapes. This noise absorbing or insulating material may be connected to the inner tire surface or to the rim surface facing into the tire. Thus, the material is not externally visible once the tire has been mounted on the wheel rim.

Abstract: Sound is uniformly distributed in a confined space such as the passenger in of an aircraft by connecting an acoustic drive member to an entire wall panel or to an entire ceiling panel of the cabin structure whereby such panels act as the membrane of a loudspeaker. By properly spacing the membrane panels the entire cabin space is filled with sound in stereophonic fashion, whereby the seating arrangement becomes independent of the loudspeaker locations and vice versa.

Abstract: A wing is secured to the body of a craft, for example an aircraft, at least t four support points interconnected in pairs by a respective clamping bolt. The metal planking of the upper and lower wing structure forms two wing forks each having a respective securing end and two forked legs. One wing fork is secured with its forked legs to the upper wing structure surface. The other wing fork is secured with its forked legs to the lower wing structure surface. Each of the four support points of the craft body forms a forked bracket so that each support point has two half brackets. The half brackets of a pair are vertically aligned so that the respective clamping bolt may pass through these aligned half brackets and through the respective securing ends of the wing forks extending into the space between two half brackets.

Abstract: A rotor blade, for example for a windmill, comprises a plurality of blade ctions between a blade root and a tip. The sections are interconnected by tensioning members such as steel cables or the like, preferably extending through the blade sections. Thus, each section may be manufactured individually and all components may be assembled at the construction site, whereby relatively large windmill rotors may be constructed.

Abstract: A force or load transmitting connecting element is provided at its ends w bolt eyes for receiving bolts which secure the connecting element to another structural component also provided with complementary bolt eyes or for securing a wing to an aircraft body. The bolt eyes must be capable of taking up compression and/or tension loads. For this purpose at least one reinforcing bridging web is located between at least two bolt eyes. The bridging web extends with its main plane perpendicularly to the central axes of the bolt eyes and loops at least partially around at least one of the bolt eyes. The bolt eyes are constructed as metal bushings. Thus, the bridging web braces the bolt eyes relative to each other.

Abstract: In an air inlet for a gas turbine jet propulsion plant in which the inlet annel is curved, separation flow is generated near the inner wall surfaces of the inlet at certain angles of attack. A flow guide fence is employed which reaches into the air inlet channel a small extent radially so that separation flow is caused to follow the channel and substantially dissolves itself by the time it reaches the compressor entrance so that flow to the compressor is substantially homogeneous.

Abstract: A coupling or clutch type element for connecting a driving member to a drn member, in a universal manner allowing for axial and/or angular displacements between the two members, is made by laminating sheets cut from preimpregnated fiber compound webbings onto a subsequently removable core. The sheets are placed in consecutive, overlapping layers with a predetermined fiber orientation. The initial tackiness holds the blanks and layers of sheets together. The assembly of laminates is less compressed in a mold and cured which provides the required bonding and operational strength. After removing the coupling element from the mold the core is removed, for example, by melting or washing. The resulting product does not require any subsequent machining.

Abstract: The wing blades of a helicopter rotor each are connected to the rotor hub a connection, e.g. a spar being .fwdarw..rarw. including a hinge which is at least fictitious to permit lead-lag movements of the blades <yielding relative to torsion to permit the blade angle adjustment>. A rod, which is stiff in the lead-lag direction and yielding against torsion, is connected in parallel to the connection between the blade root and the rotor hub. One connection of the rod is rigid, for example the connection to the blade root. The other connection of the rod is elastically yielding substantially only in the plane of the rotor whereby a substantial damping of blade movements in the lead-lag direction is accomplished.

Abstract: A flying object is precisely steered by determining the position of the fng object with the aid of a trigonometric calculation. For this purpose pulse signals emitted in synchronism from two ground stations are received by the flying object and the time difference between the two arrivals is measured. The flying object is also equipped with a clock which is synchronized with the clocks of the two ground stations. Thus, the emitting times are available in the flying object. Based on the measured time difference between the receipt of the two pulses and on the given emission time the coordinates of the actual position of the flying object are calculated. The calculated position coordinates are compared with position coordinates of a rated course stored in the airborne equipment whereby a course deviation signal is calculated. The course deviation signal is then applied to the steering mechanism of the flying object to bring the latter back onto the rated course.

Abstract: The present connecting device for joining sheet metal components has a la of synthetic material at least in the area of the contact surfaces with neighboring components thus effectively preventing contact corrosion.

Abstract: The wings of a rotary wing aircraft comprise, for example, four wing blades orming two pairs of wing blades whereby the blades of a pair are located diametrically opposite each other. The blades of a pair are connected to each other by a spar extending from wing blade to wing blade. The spar is operatively secured to the rotor head. Each spar has between the rotor head and the respective wing blade a zone with a torsion yieldability larger than in the spar outside said zone. A beam stiff against bending, bridges the zone, referred to as a torque soft zone, from the wing blade toward the rotor head except for a small flexible section between the rotor head and the radially inner end of the beam. The flexible section permits the blade flapping movements and the blade lead-lag movements.

Abstract: Cable harnesses are manufactured with a so-called cable head arranged on a able laying carriage. The cable head is controlled by an electronic data processor and continuously lays a cable running off a coil or spool, about pins on a cable laying table or pallet. A plurality of such coils or spools are mounted in a cable magazine arranged for cooperation with said cable laying table. Any one of the cables on the coils may be drawn into the cable head which is equipped with cable marking tools and with cable buffer tools. The cable being laid is marked and for this purpose it is "buffered" to such an extent, that a dwell time is obtained sufficient for the marking operation. The buffering takes place first to form a loop. The cable length stored in the loop is used up during the marking so as not to interrupt the feed advance of the cable during its marking.

Abstract: A built-in connector element is constructed for being anchored in sandwich ype compound panels. For this purpose the connector element has a central threading for cooperation with further connector components and a body with corners forming anchoring fins for holding the connector element in the compound panel. The cornered body is arranged substantially concentrically relative to said threading and has a rounded flange merging into the anchoring fins. The anchoring fins are so dimensioned that the circle enclosing the outer corners of the fins has a diameter which is equal or larger than the diameter of the flange. In one embodiment the central threading is provided directly in the cornered body. In the other embodiment a threaded member is laterally displaceable in the hollow cornered body, whereby the initial insertion of a screw is made easier.