Abstract: A door assembly, particularly for doors of passenger aircraft, includes a door frame, a door having a door body hingedly installed in the door frame, at least one hooking pintle attached to the door frame or an edge of the door body extending along a pintle axis, and at least one door latch connected to an edge of the door body or the door frame, respectively, the door latch having a substantially C-shaped latch body configured to rotate around an axis parallel to the pintle axis of the hooking pintle. The door assembly further includes a bistable latch and hook mechanism configured to catch the door latch in hooking engagement with the hooking pintle and to retain the door latch in a direction perpendicular to the door body in an overcenter position.

Abstract: A folding table for an aircraft comprising a supporting device for a tabletop, a pull-out device for moving the supporting device from a vertical stowing position to a horizontal usage position via a pull-out position, wherein the pull-out device has a guiding device for guiding the supporting device between the stowing position and the pull-out position, wherein the guiding device has a linear first guide track for a first guide element on the supporting device and a second guide track for a second guide element on the supporting device, which second guide track has linear and arcuate segments, wherein the supporting device is slid along the linear segment of the second guide track of the guiding device from the stowing position into the pull-out position, and is pivoted along the arcuate segment of the second guide track of the guiding device from the pull-out position into the usage position.

Abstract: A folding table for an aircraft comprising a supporting device for a tabletop, a pull-out device for moving the supporting device from a vertical stowing position to a horizontal usage position via a pull-out position, wherein the pull-out device has a guiding device for guiding the supporting device between the stowing position and the pull-out position, wherein the guiding device has a linear first guide track for a first guide element on the supporting device and a second guide track for a second guide element on the supporting device, which second guide track has linear and arcuate segments, wherein the supporting device is slid along the linear segment of the second guide track of the guiding device from the stowing position into the pull-out position, and is pivoted along the arcuate segment of the second guide track of the guiding device from the pull-out position into the usage position.

Abstract: A door assembly, particularly for doors of passenger aircraft, includes a door frame, a door having a door body hingedly installed in the door frame, at least one hooking pintle attached to the door frame or an edge of the door body extending along a pintle axis, and at least one door latch connected to an edge of the door body or the door frame, respectively, the door latch having a substantially C-shaped latch body configured to rotate around an axis parallel to the pintle axis of the hooking pintle. The door assembly further includes a bistable latch and hook mechanism configured to catch the door latch in hooking engagement with the hooking pintle and to retain the door latch in a direction perpendicular to the door body in an overcenter position.

Abstract: A fuselage segment for an aircraft fuselage includes a wall with a closed cross section, a first cabin floor, a second cabin floor, and a cargo hold floor. The first cabin floor, the second cabin floor, and the cargo hold floor are vertically spaced apart from each other and connected to the wall. A first passenger region is arranged above the first cabin floor, a second passenger region is arranged above the second cabin floor, and a cargo region is arranged above the cargo hold floor. The cargo region is dimensioned in such a manner that for at least four passenger seats a maximum of 1 m3 of cargo hold volume is provided. In this manner an existing aircraft fuselage can be designed in a demand-oriented manner so that it can accommodate two or more passenger regions.

Abstract: A rotational speed superimposition device for a vehicle steering system is proposed, having an output shaft (2) which is aligned towards the input shaft (1) in its axial direction (22), having a first carrier arrangement (6) which rotatably positions the output shaft (2) and the input shaft (1) at least partly supported, having an auxiliary drive (5, 10) with a rotor (5) which is connected in an operative, torque-proof manner to a first gear element (4) of a superimposition gear unit (7), and having a second carrier arrangement (11) which is arranged in a fixed manner on the chassis and which holds the auxiliary drive (5, 10) and supports the rotor (5) so that it can rotate, wherein the rotor (5) of the auxiliary drive (5, 10) coaxially surrounds the output shaft (2) and/or the input shaft (1), and wherein the superimposition gear unit (7) transmits the rotational speed of the rotor (5) to the rotational speed of the output shaft (2) at a rotational speed ratio that is less than 1.

Abstract: The present invention relates to a specially designed hinge mechanism, which makes it possible to construct an aircraft door that can be fitted in a fuselage so as to be displaceable and swivellable on the fuselage. Furthermore, the invention relates to an aircraft door comprising at least one such hinge mechanism designed in this way, to a fuselage with at least one aircraft door that is linked to at least one hinge mechanism, designed in this way, on the fuselage, as well as to the use of at least one hinge mechanism for installation of an aircraft door at a fuselage.

Abstract: A rotational speed superimposition device for a vehicle steering system is proposed, having an output shaft (2) which is aligned towards the input shaft (1) in its axial direction (22), having a first carrier arrangement (6) which rotatably positions the output shaft (2) and the input shaft (1) at least partly supported, having an auxiliary drive (5, 10) with a rotor (5) which is connected in an operative, torque-proof manner to a first gear element (4) of a superimposition gear unit (7), and having a second carrier arrangement (11) which is arranged in a fixed manner on the chassis and which holds the auxiliary drive (5, 10) and supports the rotor (5) so that it can rotate, wherein the rotor (5) of the auxiliary drive (5, 10) coaxially surrounds the output shaft (2) and/or the input shaft (1), and wherein the superimposition gear unit (7) transmits the rotational speed of the rotor (5) to the rotational speed of the output shaft (2) at a rotational speed ratio that is less than 1.

Abstract: The present application relates to a specially designed hinge mechanism (4) which makes it possible to construct an aircraft door (2) that can be fitted in a fuselage (3) so as to be displaceable and swivellable on the fuselage (3). Furthermore, the invention relates to an aircraft door (2) comprising at least one such hinge mechanism (4) designed in this way, to a fuselage (3) with at least one aircraft door (2) that is linked to at least one hinge mechanism (4), designed in this way, on the fuselage (3), as well as to the use of at least one hinge mechanism (4) for installation of an aircraft door (2) on a fuselage (3). The hinge mechanism (4) essentially comprises a displacement mechanism (5, 6) as well as a telescopic scissor-type mechanism (7-12). The displacement mechanism (5, 6) can be linked to an aircraft door (2) and is kinematically designed such that as a result of its activation the aircraft door (2) can be displaced from its home position in the direction of the fuselage (3).

Abstract: A method for determining the ignition angle is provided, in which modifications of manipulated variables which have an influence on the knock limit, and therefore on the optimum ignition angle as well, are dynamically taken into account. To this end, a base ignition angle is first determined, based on the instantaneous engine speed and load. As part of a downstream knock control, a first ignition angle adjustment in the retard direction is determined when knocking has been detected. As part of a knock limit control, a second ignition angle adjustment is also determined when at least one manipulated variable influencing the knock limit changes, with the type of the second ignition angle adjustment, i.e., advancing or retarding, depending on the manipulated variable and its modification.

Abstract: The present invention relates to a specially designed hinge mechanism (4), which makes it possible to construct an aircraft door (2) that can be fitted in a fuselage (3) so as to be displaceable and swivellable on the fuselage (3). Furthermore, the invention relates to an aircraft door (2) comprising at least one such hinge mechanism (4) designed in this way, to a fuselage (3) with at least one aircraft door (2) that is linked to at least one hinge mechanism (4), designed in this way, on the fuselage (3), as well as to the use of at least one hinge mechanism (4) for installation of an aircraft door (2) at a fuselage (3).

Abstract: A method for determining the ignition angle is provided, in which modifications of manipulated variables which have an influence on the knock limit, and therefore on the optimum ignition angle as well, are dynamically taken into account. To this end, a base ignition angle is first determined, based on the instantaneous engine speed and load. As part of a downstream knock control, a first ignition angle adjustment in the retard direction is determined when knocking has been detected. As part of a knock limit control, a second ignition angle adjustment is also determined when at least one manipulated variable influencing the knock limit changes, with the type of the second ignition angle adjustment, i.e., advancing or retarding, depending on the manipulated variable and its modification.

Abstract: A method for operating an internal combustion engine and a corresponding device are described, in which reference pulses are generated synchronously with respect to the cyclical movement of at least one part of the internal combustion engine. At least one event moment for the occurrence of at least one event is calculated by an output unit at specific, definitively preset time intervals of the cyclical movement. Moreover, an independent clock-pulse generator is provided which generates clock pulses, the interval of the clock pulses being independent of the movement, and the interval of the clock pulses being smaller than the interval of the reference pulses. The at least one event moment is expressed as the number of clock pulses of the independent clock-pulse generator, and the at least one event is triggered upon reaching the number of clock pulses.

Abstract: A method for operating an internal combustion engine and a corresponding device are described, reference pulses (45) being generated synchronously with respect to the cyclical movement of at least one part of the internal combustion engine. At least one event moment for the occurrence of at least one event is calculated by an output unit (24) at specific, definitively preset time intervals of the cyclical movement. Moreover, an independent clock-pulse generator (25) is provided which generates clock pulses, the interval of the clock pulses being independent of the movement, and the interval of the clock pulses being smaller than the intervals of the reference pulses. The at least one event moment is expressed as the number of clock pulses of the independent clock-pulse generator, and the at least one event is triggered upon reaching the number of clock pulses.

Abstract: A method for manufacturing chip stacks in which wafers are stacked one on top of the other. The wafer is provided with an adhesive foil on its bottom, and is subsequently cut into chips so that the adhesive foil remains intact and the chips adhering to the adhesive foil are stacked one on top of the other. A first layer of chips is reversibly attached to a baseplate, the adhesive foil is removed, the next layer of chips is attached to the bottom side of the chips already fastened to the baseplate, the adhesive foil is removed, and the last two steps are repeated until the desired number of chips is stacked one on top of the other.

Abstract: An arrangement for switching a high-voltage switch by optical energy is proposed. The high-voltage switch comprises a number of controllable semiconductor elements, which switch through when illuminated with light. The light energy is transmitted via a light guide or optical fiber rod, and the angle between the light guide or optical fiber rod and the high-voltage switch is from 5.degree. to 20.degree., and the light guide or optical fiber rod is cut obliquely on its end toward the high-voltage switch, producing an elliptical cross section.

Abstract: An ignition device for internal combustion engines with stationary high-voltage distribution, having at least one ignition coil (11), wherein a controllable switch (12) is disposed in series with the primary winding (10) and is triggerable by a control unit (13), wherein at least one high-voltage break-over diode (HKD), which comprises a plurality of break-over diode chips, is disposed in each secondary-side ignition branch between the high-voltage-side end of the secondary winding (14) and a spark plug (ZK1, ZK2, . . . , ZKn). A switch triggered by the control unit during the ignition coil charging operation makes a conditioning flow possible through the high-voltage break-over diode (HKD), which current in the high-voltage break-over diode floods the blocking region with charge carriers (38) (FIG. 1).

Abstract: A high-voltage breakover diode is proposed, which takes on the function of an ignition voltage distributor of an internal combustion engine having solid-state highvoltage distribution. The high-voltage breakover diode comprises a cascade of breakover diode chips, a polyimide layer having recesses in the region of the cathode connection being provided between the individual breakover diode chips produced using planar technology, in each case on the top of the breakover diode chips, and the mechanical and electrical connection of the individual breakover diode chips being effected by means of a conductive adhesive (FIG. 3).

Abstract: A device for operating a gas-discharge lamp includes a starting member and a power member for supplying energy to the lamp. A switch is arranged between the lamp and the power member and connects the power member with the lamp subsequent to the initiation of the starting process.

Abstract: A high voltage switch can be used in an internal combustion engine ignition system to switch a high voltage through to a spark plug upon illumination of a light-sensitive portion of the switch. The high voltage switch includes two sub-stacks of break-over diodes, with the diodes of the two sub-stacks having different properties. The break-over diodes of a first, illuminated sub-stack of the high voltage switch have a break-over voltage with a low dependence on temperature, whereas the break-over diodes of a second, unilluminated sub-stack have a low break-over current with tight tolerances.