Abstract: A system for generating solar energy utilizes a plurality of solar radiation absorption bodies formed as spherical balls which interact with solar radiation focalization devices which constitute paraboloid mirrors in order to effect heating of the spherical balls by the solar radiation which is concentrated at an irradiation position defined by the paraboloid mirrors. The heated balls are transported to a heat accumulator and after the heat has been absorbed therefrom they are returned to the focalization mirrors. At the mirrors, balls are held in holding devices until a heated ball leaves the irradiation position and switch devices operate to provide new balls to a vacant holding position. A feed and return system for transporting the balls between the accumulator and the focalization mirrors may comprise thermally insulated pipes and the balls may be moved by gravity feed or by a compressed air system.

Abstract: A laminar panel assembly which is particularly useful in space vehicles for contact with solar cells includes a first and a second cover layer, a supporting core structure interposed between the cover layers and at least one force infeed element disposed within the core structure between the cover layers. The force infeed element includes at least one solid central piece for punctiform load infeed, and shear webs extending from the central piece radially outwardly in a branched formation such that the number of shear webs increases with increasing radial distance from the central piece.

Abstract: A method of producing an underground cavity in a driving shield advance operation comprises, prior to excavation, forming an annular slot corresponding to the contour and wall thickness of the shield ahead of the shield by using hot gas jets to form the slot and to separate a core from the surrounding rock formation, advancing the shield into the annular slot, and breaking out the core under the protection of the shield. The device for producing the underground cavity comprises a tubular drive shield adapted to be advanced into the cavity and having an interior support wall on which is rotatably supported a support member having an arm carrying a gas jet lance. The gas jet lance advantageously includes at least one gas nozzle directed forwardly to form an inwardly extending cavity ahead of the shield, and one or more nozzle discharges directing the gas laterally.

Abstract: A method of producing fractures or gaps in geological formations of crystalline rocks in order to utilize the heat of the earth surrounding the gaps, comprises, drilling at least one bore into the rock, producing a pressure fluid in the bore adjacent the rock by introducing pressure gas-producing propellants into the bores to a location within the rock formation and reacting the pellants after they have been sealed off from the top of the bore and discharging the fluid pressure into the bore to put the rock under a pressure above its breaking limit so as to produce a large surface gap. The apparatus advantageously comprises a pressure gas generator which operates from a monergolic propellant which is decomposed catalytically and which includes a sealing bellows arranged around a reaction chamber at the bottom of the bore which is sealed at the upper end or to the rear and is connected with the pressure gas chamber and an outlet into the forming gap having a non-return valve therein.

Abstract: A programmable binary correlator with one-digit, digital sampling is disclosed. The binary correlator includes input comparators for converting a signal to digital form, each comparator connected to a storage unit. The storage units are connected to programmable counters which, in turn, coact, through a control element, with additional counters. The various counters, control element and storage units cooperate with a unit for supplying programmed signals. A clock signal generator is present to control the correlator timing and supply necessary pulse signals. By storing digital representations of two input signals in the storage units in a particular way, by comparing these stored signals bit by bit in a coincidence tester, by repeating the comparison by repeatedly shifting one stored signal relative to the other, and by storing the number of coincidences in a final counter, a correlation of the two input signals is made. An analog correlator employing a plurality of such binary correlators is also disclosed.

Abstract: A rotor blade formed of a fiber-reinforced plastic material is constructed for the absorption of at least one of longitudinal forces and bending forces. The interior of the blade is formed of an elongated bundle of fiber strands forming a loop intermediate its ends. The loop defines one end of the longitudinally extending blade. The bundle has two limb portions extending from the loop and forming, adjacent the loop, a transition portion followed by a neck portion and then a blade portion. A skin encloses the blade outwardly from the loop. A layer of fiber strands extends around the outer surface of the loop and between the skin and the limb portions at least in the transition portion. In the region of the loop the fiber strands extend in parallel relation with the fiber strands in the bundle, however, in the transition portion the fiber strands in the layer extend angularly across the longitudinal axis of the blade.

Abstract: A method and device is disclosed for increasing the hit probability of guided missiles exposed to jamming by double or multiple targets. In particular, the missiles are guided by the proportional navigation principle and have a follow-up target-seeking head. With the addition of a plurality of tracking filters, means for performing data analysis and means for performing data control to a conventional missile guidance system, signals from the target-seeking head or the missile may be analyzed to provide recognition of double or multiple target situations. Once recognition of the double or multiple target situation is made, the flow of data for controlling the guidance and target-seeking head follow is corrected to keep the missile permanently on the target.

Abstract: A heat recovery system for use with a rotatable cylindrical kiln having a curved sidewall surface and which is adapted to be fired, for example, by a burner supplied through a fuel supply line with fuel oil, comprises, at least one segment member which overlies and is spaced from the kiln curved sidewall surface and which defines a heat radiation absorbing surface. A coolant circulating system is connected to the segment member and a coolant is circulated therethrough and then into a separate heat exchanger which is used for recovering the heat. The heat exchanger may be employed, for example, to preheat the oil which is delivered to a burner for firing the kiln or it may be used in a separate system requiring heat. A segment member is advantageously mounted on an undercarriage so that it may be moved toward or away from the kiln surface in accordance with the heat exchange requirements.

Abstract: The magnets supporting a magnetic suspension vehicle are vibrationally isolated from the vehicle body by mounting a number of the magnets on each chassis with individual spring arrangements whose reactive moments are greater than the pitch and roll moments tending to deflect the magnets.

Abstract: A straight flow seat valve, comprising, a valve housing with a valve chamber therein having an inlet at one end and an outlet at the opposite end which is coaxial with the inlet. A control cylinder is supported in the valve chamber between the outlet and inlet and has a control fluid inlet extending out of the housing for the admission of a control fluid into the chamber in order to move a piston against a spring-biasing force so as to shift a seat body having a seat surface in engagement with a seat adjacent the outlet end so that it is lifted off the seat to open the valve. The seat body is advantageously streamlined at each end to permit flow around it from the inlet around the valve and out through the outlet. In the pressureless state, the spring urges the surface of the seat body onto the valve seat to close the valve.

Abstract: A wide-band vibration damper for damping sound propagating in a solid body includes at least one horn member having a broad end or side and a tapering end. The broad horn side or end is rigidly connected to the solid body which is to be dampened in its vibration. The tapering end of the horn member is connected to a supporting rigid point through a damping material such as a foam material or the like.

Abstract: The proximity fuse is incorporated in a warhead carried by a missile. This warhead comprises several active or passive bodies, which consist of preformed splinters or shaped charges. The proximity fuse comprises a circuit for producing an ignition signal to start the decomposition of the warhead when a distance is reached between the warhead and a target, for instance a missile. This distance is determined by using electromagnetic waves. The circuit comprises means for determining the time t.sub.A, which will elapse before the warhead encounters the target. Moreover, the circuit comprises means for storing a constant reference time t.sub.B, which is fixed in such a way that the active or passive bodies released within a certain space sector when the warhead decomposes, will be scattered in a certain space, i.e. they will cover this space in front of the target within this reference time. The circuit also comprises means for comparing the calculated time with the constant reference time being provided.

Abstract: An airfoil or wing is connected to the body of an aircraft or spacecraft through a main connector comprising metal and nonmetal components. Tension load take-up loops and a pressure load take-up core are arranged or held in a metal grommet which in turn is centered relative to and integrated with a main connector bushing. Thus, the tension loads are solely introduced into the wing structure through the tension loops and pressure loads are taken up solely by the pressure core, whereby the advantages of fiber compound materials are optimally utilized.

Abstract: An infantry projectile includes an elongated projectile body having a cylindrical or frusto-conical surface concentrically arranged about its longitudinal axis. The projectile body has a leading end and a trailing end each extending transversely of the longitudinal axis. The leading end is disposed at an oblique angle to the longitudinal axis for affording a trimming action on the projectile when it is in flight. A flow control projection is provided on the surface of the projectile body between its ends so that the aerodynamic center of the projectile is located below its center of gravity when the flow control projection is located on the lower surface of the projectile body and in a vertical plane extending through the longitudinal axis of the body.

Abstract: The present variable volume resonators have an inner volume enclosed by wall members constructed as Belleville springs. The wall members confine in said volume a pressure which is reduced relative to atmospheric pressure, whereby the springs have a small spring constant in response to a reduced pressure load. Each resonator is so constructed that it has a relatively large resonating surface and a relatively low resonating mass. The sound damping effect of the resonator volume is enhanced by means of various types of damping devices including a high viscosity residual gas, wire mesh members, or liquid drops in the volume interior. The present resonators also comprise features for compensating air pressure and/or the resonance frequency.

Abstract: A device for extracting crude oil out of an extraction bore of a previously tapped deposit, comprises, a combustion chamber having at least one reaction chamber portion and an evaporation chamber portion arranged in axial relationship with a constricted nozzle portion therebetween. Advantageously, an additional constricted nozzle portion separates a turbulence chamber from a front reaction chamber and the second constriction separates the front reaction chamber from a rear evaporation chamber. The evaporation chamber in turn feeds through a nozzle section to a narrow discharge into the extraction bore. A fuel and chemical oxygen or an oxygen carrier are directed into the combustion chamber preferably in front of the first constriction and forms high temperature combustion gases into which the water is directed in a manner to intermix the water with the combustion gases and to form superheated steam which is then discharged into the extraction bore.

Abstract: The present apparatus is used for ascertaining the individual weight of any type of load including that of passengers and of hand baggage, that is added to the total payload of an aircraft. Each individual weight is ascertained and, if desired, displayed and added up to ascertain the total weight. For this purpose a weight sensing device such as a group of load cells or the like including a platform is arranged at the entrance to the freight or baggage compartment and, in a passenger aircraft at each passenger entrance door inside the aircraft. The weight sensing device provides an electrical signal for each weight unit that passes the platform into the aircraft. The weight representing electrical signal is supplied to an adder and to a display unit where the individual weights are displayed as well as the total weight.

Abstract: A shaft drive alternately for both directions of rotation, comprises, a shaft rotatably supported on bearings having first and second turbines connectable thereto, each including a respective first and second turbine wheel freely rotatable on the shaft in respective opposite first and second directions. The turbine wheels are driven by fluid which rotates the wheels in a selected direction and, in addition, displaces the turbine wheels so that a friction disc carried thereby is engaged with a respective first and second clutch to connect it to the shaft to impart the selected direction of rotation. When the turbine is stopped by not directing the fluid into the blades, in which case the clutch mechanism is moved out of engagement and the turbine wheel may run free of the shaft, the second turbine wheel may be connected in a similar manner by effecting engagement of the associated second clutch with the shaft when the fluid is directed to the second turbine for rotating the turbine wheel.

Abstract: The present system automatically stabilizes the travel direction of an aircraft rolling out after touchdown on a runway. A corrected difference control signal is supplied to the steering mechanisms of the aircraft, including, if desired, the brake system. The control signal is generated in a comparator or transducer which receives at its inputs an actually measured signal representing changes in the travel direction of an aircraft, and a rated signal to produce a combined steering signal which is supplied to the nose wheel steering and/or to the wheel brakes.

Abstract: A rotor, especially for rotary wing aircraft, is constructed without flapping hinges and without lead-lag hinges. The rotor comprises a rigid rotor head and rotor blades secured to the rotor head by flexible coupling rods, for example, made of fiber reinforced composite material. One end of each rod is secured to the rotor head. The other end of each rod is secured to the root of the respective rotor blade. The rods are so arranged that their central longitudinal axes coincide with a generatrix of two coaxial cones having a central axis. One of the cones is located with its base in the respective rotor blade while the other cone is located with its base in the rotor head. This type of structure is surprisingly simple, yet capable of transferring substantial forces between the rotor head on the one hand and the rotor blades on the other hand.