Abstract: The present invention concerns an ultrasonic welding installation comprising an ultrasonic vibration unit having a sonotrode and a converter, wherein the sonotrode and the converter are arranged in mutually adjacent relationship along a longitudinal axis and the ultrasonic vibration unit can be caused to resonate with an ultrasonic vibration in the direction of the longitudinal axis with a wavelength ?/2, wherein there is provided a holder for holding the ultrasonic vibration unit.

Abstract: A method for electrical testing of an electrical circuit for defects, all electrical or electronic parts are measured simultaneously, so an electrical image of the electrical circuit is received by a control/evaluation unit, in which an electrical excitation signal of an electrical current or an electrical voltage is applied simultaneously by the control/evaluation unit and a plurality of driver circuits at a plurality of test points of the electrical circuit, which test points may be arranged in any way. The electrical excitation signals applied via the driver circuits differ with regard to their spectral characteristic. The electrical current flowing in the particular test point and the resultant electrical voltage are recorded synchronously with regard to a waveform in relation to an electrical ground potential, and subsequently parameters of the parts and their electrical connections are calculated by the control/evaluation unit.

Abstract: The present invention relates to a method for electrical testing of an electrical circuit for defects, all electrical or electronic parts are measured simultaneously, so an electrical image of the electrical circuit is received by a control/evaluation unit, in which an electrical excitation signal of an electrical current or an electrical voltage is applied simultaneously by the control/evaluation unit and a plurality of driver circuits at a plurality of test points of the electrical circuit, which test points may be arranged in any way. The electrical excitation signals applied via the driver circuits differ with regard to their spectral characteristic. The electrical current flowing in the particular test point and the resultant electrical voltage are recorded synchronously with regard to a waveform in relation to an electrical ground potential, and subsequently parameters of the parts and their electrical connections are calculated by the control/evaluation unit.

Abstract: A handling system for handling objects in a vehicle comprises a storage apparatus that is positionable outside a vehicle cabin, an access device that is positionable in a vehicle cabin, and a transport device for transporting objects between the storage apparatus and the access device. The storage apparatus comprises a storage space and a connection station that is connectable to the transport device, wherein the storage apparatus comprises at least one drive device for moving carriers on which objects to be stored are held. The handling system comprises at least one guiding device that with the drive device guides the carriers on at least one circular path within the storage space. The storage space thus comprises a vertical flat shape that results in a significantly smaller reduction in the available cargo volume in a vehicle, while at the same time maximizing the design space available for passenger seats.

Abstract: The invention relates to the monitoring of the landing flaps on an airfoil (2) for an aircraft (1), and to an aircraft (1) having such an airfoil (2). The airfoil (2) has a wingbox (3), a support (5) which is mounted relative to the wingbox (3) such that it can rotate with respect to a flap rotation axis (7), a flap (4) which is attached to the support (5) and rotates with respect to the flap rotation axis (7) during rotation of the support (5) relative to the wingbox (3), a movement mechanism (8) which is coupled to the support (5) in order to set an angle position of the flap (4) with respect to the wingbox (3) and a measurement apparatus (18) for detection of the angle position of the flap (4). The measurement apparatus (18) has a rotation sensor (19), which is arranged on the support (5), and a four-element coupling transmission (22, 24, 26, 27) which couples the rotation sensor (19) to the movement mechanism (8).

Abstract: With a device for error detection of adjustable flaps on aircraft wings, it is proposed that each flap is provided with a tube as a transmission element arranged in the wing span. The tube is connected fixedly at one end with the flap and is rotatably held. On the free end of the tube, a measuring arm is fixedly arranged on the tube and a sensor fixed to the flap structure is arranged. When an error occurs, the flap twists, whereby a distance change between the sensor and measuring arm occurs. The signals of the sensor are transmitted for error localization of each flap to an evaluation device, which switches off the drive via a control device with occurring errors.

Abstract: The invention relates to the monitoring of the landing flaps on an airfoil (2) for an aircraft (1), and to an aircraft (1) having such an airfoil (2). The airfoil (2) has a wingbox (3), a support (5) which is mounted relative to the wingbox (3) such that it can rotate with respect to a flap rotation axis (7), a flap (4) which is attached to the support (5) and rotates with respect to the flap rotation axis (7) during rotation of the support (5) relative to the wingbox (3), a movement mechanism (8) which is coupled to the support (5) in order to set an angle position of the flap (4) with respect to the wingbox (3) and a measurement apparatus (18) for detection of the angle position of the flap (4). The measurement apparatus (18) has a rotation sensor (19), which is arranged on the support (5), and a four-element coupling transmission (22, 24, 26, 27) which couples the rotation sensor (19) to the movement mechanism (8).

Abstract: With a device for error detection of adjustable flaps on aircraft wings, it is proposed that each flap is provided with a tube as a transmission element arranged in the wing span. The tube is connected fixedly at one end with the flap and is rotatably held. On the free end of the tube, a measuring arm is fixedly arranged on the tube and a sensor fixed to the flap structure is arranged. When an error occurs, the flap twists, whereby a distance change between the sensor and measuring arm occurs. The signals of the sensor are transmitted for error localization of each flap to an evaluation device, which switches off the drive via a control device with occurring errors.

Abstract: Flaps, for example leading edge flaps and/or trailing edge flaps of an aircraft wing, are driven and adjusted by respective drive units. Drive shafts of neighboring flaps are coupled to each other by a differential gear. The differential gear is thus coupled to a main drive shaft which is driven by a main drive unit. Additionally, the differential gear is coupled to a secondary drive unit. The main drive power and the secondary drive power and thus the respective flap motions are super-imposable on each other, which permits operating the flaps independently of each other or in synchronism with each other.

Abstract: An aircraft flap (or slat) drive apparatus includes first and second centralized drive units that respectively rotationally drive first and second drive lines in both wings. The first drive line includes shaft segments connected end-to-end by selectively engageable separating devices. The outboard ends of the first and second drive lines are coupled through one of the separating devices, in each wing. At least one actuator mechanism connects each flap to a respective shaft segment of the first drive line, and converts the drive line rotational motion to a flap translational motion. If a component breaks, jams, or otherwise fails, it is isolated by disengaging the two adjacent separating devices with the faulty component therebetween, so that the rest of the apparatus remains functional. Each one or both of the drive units can drive one or more or all of the flaps through the interconnected first and second drive lines.

Abstract: Flaps, for example leading edge flaps and/or trailing edge flaps of an aircraft wing, are driven and adjusted by respective drive units. Drive shafts of neighboring flaps are coupled to each other by a differential gear. The differential gear is thus coupled to a main drive shaft which is driven by a main drive unit. Additionally, the differential gear is coupled to a secondary drive unit. The main drive power and the secondary drive power and thus the respective flap motions are super-imposable on each other, which permits operating the flaps independently of each other or in synchronism with each other.

Abstract: An aircraft flap (or slat) drive apparatus includes first and second centralized drive units that respectively rotationally drive first and second drive lines in both wings. The first drive line includes shaft segments connected end-to-end by selectively engageable separating devices. The outboard ends of the first and second drive lines are coupled through one of the separating devices, in each wing. At least one actuator mechanism connects each flap to a respective shaft segment of the first drive line, and converts the drive line rotational motion to a flap translational motion. If a component breaks, jams, or otherwise fails, it is isolated by disengaging the two adjacent separating devices with the faulty component therebetween, so that the rest of the apparatus remains functional. Each one or both of the drive units can drive one or more or all of the flaps through the interconnected first and second drive lines.

Abstract: A process for feeding bulk material onto a belt of a rotary hearth furnace, which has hoods that cover the hearth belt in such a manner as to form a ring.The bulk material is deposited on a transport device at a layer thickness proportionately dependent on the distance to the rotary hearth center. The transport speed of the transport device is set at a certain value; the surface of the bulk material is smoothed; and then the bulk material is distributed at a constant layer height over the entire width of the hearth belt.

Abstract: A process and installation for preheating scrap containing organic matter, in which flue gas is afterburned in an afterburner combustion chamber at a temperature at more than 1200.degree. C. The after-burned hot flue gases are guided, without being cleaned, via a heat exchanger. Fresh intake air is heated in the heat exchanger by sensible heat of the after-burned hot flue gases. A first portion of the heated intake air at a temperature above an ignition temperature of organic matter is guided in adjustable amounts through at least one basket filled with scrap. Another portion of the heated air exiting the heat exchanger is made available in adjustable quantities to the afterburner as hot blast and/or mixed in the another portion of heated intake air with the after-burned hot flue gases.

Abstract: A flap system along the trailing edge of a transonic aircraft wing which system includes segments arranged in span direction, a driving system for protraction and retraction of the segments includes a plurality of spindle drives connected to the segments such that each segment is connected to at least two spindle drives; are controlled the spindle drives in such a manner that at least some of the drives are independently controlled from each other so that the segments can pivot on vertical axes, in addition to a regular pivoting about respective horizontal axes.

Abstract: Flaps mounted on an carriage are being protracted and retracted in relation to a aircraft wing of which the flap is a part by a drive mechanism which is to be provided for variable torque and torque limiting and, if necessary, fixing and holding the position of the flap and its drive carriage in case of failure. A branching gear is driven for the common shaft which drives the flaps of one wing and there are separate transmission paths which include in each instance output shafts from the branching gear, crank drives and thrust rods. One of the thrust rod is directly connected to the flap carrying carriage and the other one indirectly through a load switch and a connecting rod; in addition one of the output shafts of the branching gear is lead into a delta alpha brake having as a second input, the output of the principle drive shaft. The delta alpha brake stops motion of the flap carrying carriage in case there is an angle difference among its input shafts that exceeds a particular limit.

Abstract: A method for the preparation of nonalcoholic beverages, especially carbonated beverages, and an apparatus for the practice of the method. First a sugar solution of prescribed concentration is prepared by dissolving sugar in deaerated water with an oxygen content below 0.15 mg/l. The sugar solution is adjusted in an additional deaeration to an oxygen content of less than 0.1 mg/l. The deaerated sugar solution can be finally adjusted to a prescribed concentration with deaerated water and carbonated, and finally it is mixed with flavorings specific to the beverage.

Abstract: Sponge iron is produced at a shaft furnace from iron ore, preferably in the form of pellets, whereby a hot reduction gas is passed upwardly through the shaft furnace and the iron ore descends therein. The hot reduction gas is formed in part by a desulfurized fresh gas produced by partial oxidation of a hydrocarbon (generally high sulfur residual oil) and desulfurization and, in part, by recirculated exhaust gas drawn from the head of the furnace and having its carbon-oxide content reduced by about ten volume percent. The fresh gas is mixed with the recirculated exhaust gas in a volume ratio of fresh gas/exhaust gas of 0.8:1.0 to produce a cold mixed gas. The cold mixed gas is heated to a temperature of about 1000.degree. C directly before being introduced into the shaft furnace as reduction gas.

Abstract: The direct reduction of iron ore, e.g., in a shaft furnace, uses a pair of reducing-gas generating reformers which are alternately heated and functionally interchanged to produce the reducing gas. Downstream of each of the reformers is an air-preheating heat exchanger and between both reformers and the direct-reduction furnace there is provided a buffer heat exchanger. The combination reduces the fluctuations of the reducing-gas temperature at the inlet to the direct-reduction furnace and is able to maintain a reducing-gas temperature close to the desirable maximum for effective reduction.