Abstract: A semiconductor device includes a semiconductor substrate having a first dopant and a second dopant. A covalent atomic radius of a material of the semiconductor substrate is i) larger than a covalent atomic radius of the first dopant and smaller than a covalent atomic radius of the second dopant, or ii) smaller than the covalent atomic radius of the first dopant and larger than the covalent atomic radius of the second dopant. The semiconductor device further includes a semiconductor layer on the semiconductor substrate and semiconductor device elements in the semiconductor layer. A vertical concentration profile of the first dopant decreases along at least 80% of a distance between an interface of the semiconductor substrate and the semiconductor layer to a surface of the semiconductor substrate opposite to the interface.

Abstract: A semiconductor device includes a semiconductor substrate having a first dopant and a second dopant. A covalent atomic radius of a material of the semiconductor substrate is i) larger than a covalent atomic radius of the first dopant and smaller than a covalent atomic radius of the second dopant, or ii) smaller than the covalent atomic radius of the first dopant and larger than the covalent atomic radius of the second dopant. The semiconductor device further includes a semiconductor layer on the semiconductor substrate and semiconductor device elements in the semiconductor layer. A vertical concentration profile of the first dopant decreases along at least 80% of a distance between an interface of the semiconductor substrate and the semiconductor layer to a surface of the semiconductor substrate opposite to the interface.

Abstract: A method of manufacturing a semiconductor device includes providing a semiconductor substrate having opposing first and second main surfaces and first and second dopants. A covalent atomic radius of a material of the substrate is i) larger than a covalent atomic radius of the first dopant and smaller than that of the second dopant, or ii) smaller than the covalent atomic radius of the first dopant and larger than that of the second dopant. A vertical extension of the first dopant into the substrate from the first main surface ends at a bottom of a substrate portion at a first vertical distance to the first main surface. The method further includes forming a semiconductor layer on the first main surface, forming semiconductor device elements in the semiconductor layer, and reducing a thickness of the substrate by removing material from the second main surface at least up to the substrate portion.

Abstract: A method for forming a power semiconductor device is provided. The method includes: providing a semiconductor wafer grown by a Czochralski process and having a first side; forming an n-type substrate doping layer in the semiconductor wafer at the first side, the substrate doping layer having a doping concentration of at least 1017/cm3; and forming an epitaxy layer on the first side of the semiconductor wafer after forming the n-type substrate doping layer.

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 method of manufacturing a semiconductor device includes providing a semiconductor substrate having opposing first and second main surfaces and first and second dopants. A covalent atomic radius of a material of the substrate is i) larger than a covalent atomic radius of the first dopant and smaller than that of the second dopant, or ii) smaller than the covalent atomic radius of the first dopant and larger than that of the second dopant. A vertical extension of the first dopant into the substrate from the first main surface ends at a bottom of a substrate portion at a first vertical distance to the first main surface. The method further includes forming a semiconductor layer on the first main surface, forming semiconductor device elements in the semiconductor layer, and reducing a thickness of the substrate by removing material from the second main surface at least up to the substrate portion.

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 conveying device for molten metal in an injection die casting unit, has a storage container for the molten metal and a conveying duct delivering the molten metal to a mold cavity. The conveying duct includes a cylinder bore with a piston disposed in an axially adjustable manner. A collection chamber, from which the molten metal is introduced through an onward line into the mold cavity upon axial displacement of the piston, is provided for the molten metal. An annular space, which is connected via at least one filling bore to the collection chamber, is formed between the outer wall of the piston and the inner wall of the cylinder bore. The filling bore, on an end which opens into the collection chamber, is closable by means of a valve body which is connected to an adjustable valve rod which is displaceably disposed in an axial bore of the piston.

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 conveying device for molten metal in an injection die casting unit, has a storage container for the molten metal and a conveying duct delivering the molten metal to a mold cavity. The conveying duct includes a cylinder bore with a piston disposed in an axially adjustable manner. A collection chamber, from which the molten metal is introduced through an onward line into the mold cavity upon axial displacement of the piston, is provided for the molten metal. An annular space, which is connected via at least one filling bore to the collection chamber, is formed between the outer wall of the piston and the inner wall of the cylinder bore. The filling bore, on an end which opens into the collection chamber, is closable by means of a valve body which is connected to an adjustable valve rod which is displaceably disposed in an axial bore of the piston.

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.