Abstract: A manipulator apparatus carries tools for connecting drillpipes to the drillstring in a wellbore on a drilling platform. A telescopically extendable horizontal work arm is carried on a telescopically extendable vertical column, and the tools are to be mounted on a free end of the work arm. The column is manually rotatable about a vertical axis. The column and the work arm are each respectively formed of a fixed element and a telescopically extendable element. The fixed element is preferably formed of two U-profile members arranged back-to-back, and the extendable element includes an H-profile member with its web received between the webs of the two U-profile members. This forms a telescopic slide bearing of the H-profile member sliding along the two U-profile members. The hydraulic cylinders are received in the recessed spaces of the profile members.

Abstract: A thermal fuse employing a thermosensitive pellet is provided, which exhibits stabilized characteristics in a low operating temperature region. The thermal fuse includes at least a switching movable member, a thermosensitive pellet member, a pair of leads having a first lead portion and a second lead portion, and a metal casing. The thermosensitive pellet member contains a polyolefin wax. The thermosensitive pellet member is housed in the metal casing to which the pair of leads are attached. The switching movable member is operated by deformation associated with softening or melting of the thermosensitive pellet member, to attain a cut-off state between the pair of leads. The thermal fuse employing a thermosensitive pellet is suitable for an operating temperature of 50 to 180° C.

Abstract: An apparatus for heat shielding and deceleration of a spacecraft comprises an unfoldable shield of individual panels made of a high temperature resistant fiber reinforced ceramic and pivotally mounted on the outer structure of the spacecraft. An unfolding ring slides axially along the body of the spacecraft. The panels are pivotally connected to the unfolding ring by compression struts acting as toggle levers. Tension springs pull the unfolding ring axially along the spacecraft body to toggle out the compression struts so as to outwardly pivotally deploy the panels. The unfoldable shield can be arranged on the forward end or the rear end of the spacecraft relative to its flight direction upon entry into the atmosphere.

Abstract: In a milling method for producing a structural component from a raw material by chip-cutting, a milling tool is moved along at least one defined tool path for the milling. In addition to the at least one tool path, at least one collision contour is also defined. The position or orientation of the milling tool relative to the collision contour(s) is monitored. The position or orientation of the milling tool is changed and/or an error message is generated if at least one of the collision contours is damaged, i.e. intersected, by the milling tool.

Abstract: A closure apparatus is fitted onto a container opening of a drinking container with an inner space for reception of a drinking liquid. The closure apparatus includes a chamber body that defines therein a receiving chamber, the content of which is introducible into the inner space of the drinking container. The closure apparatus further includes a closure element that selectively closes a first opening of the chamber body, and an axially slidably displaceable cover element that selectively closes a second introduction opening of the chamber body. The content of the receiving chamber is releasable into the inner space of the drinking container through the second introduction opening by an axial sliding displacement of the cover element.

Abstract: A brush roll is rotatably supported by bearings in a housing of a cleaning brush tool. One of the bearings is incorporated in a removable bearing arrangement that can be rotationally fastened and removed as needed on a cylindrical end of the housing. Preferably collar elements protruding cylindrically from the removable bearing arrangement form bayonet-type catch hooks that selectively engage with bayonet-type catch elements protruding radially outwardly from the cylindrical end sleeve of the housing. A detent on the housing engages a securing element on the removable bearing arrangement to secure the engaged bayonet-type fastening arrangement against rotational release thereof.

Abstract: A circuit board (1) has a top face (2) for positioning an electronic component and a bottom face (4) used as a support on a heat-dissipating base. A plurality of heat transfer holes (12) provide heat transfer from the top face (2) to the bottom face (4). The heat transfer holes (12) are unevenly or non-uniformly distributed on the top face (2) in such a way that the top face (2) is provided with several free sectors (14) which are free of heat transfer holes (12) in order to connect the electronic component to the circuit board (1). The free sectors (14) are configured as columns or lines. A plurality of heat transfer holes (12) are placed at least along the long sides of the free sectors (14). The circuit board has a low thermal resistance between the electronic component and the heat-dissipating base.

Abstract: A fiber composite material which is particularly suitable for aircraft construction, includes inorganic mineral fibers embedded or enclosed in a metal matrix. The mineral fibers include a substantial or dominant proportion of SiO2, and/or Al2O3 and/or Fe2O3, the remainder being rock material. The fibers have a length of at least 10 mm and are oriented in parallel to one another in at least one direction. The metal matrix is made of aluminum, aluminum alloys, magnesium, magnesium alloys, titanium or titanium alloys. These matrix metal alloys contain a substantial or dominant proportion of the respective metal. The fibers are preferably coated with particles of the matrix metal and bonded to one another to form fiber films or fiber sheets which are then laminated between sheets of matrix metal.

Abstract: Aircraft passengers who require a therapeutic oxygen supply independently of the prevailing cabin pressure, as distinguished from an emergency oxygen supply that depends on an inadequate cabin pressure, can breath therapeutic oxygen and/or emergency oxygen depending on the situation, through the same therapeutic oxygen masks. For this purpose a control accessible to the crew is used to connect a therapeutic oxygen supply to the emergency oxygen distribution system of the aircraft, whereby the source of oxygen is used either partially for therapeutic purposes or fully for emergency purposes.

Abstract: A control device for arrangement in a fluid environment includes a housing, with a housing lid (1) for accommodating sensors and a housing shell (2) for receiving at least one control unit (3). The control device further includes at least one device (4) for electrically connecting the sensors to the control unit (3) as well as at least one sealing element (5) for sealing the housing shell (2) against the fluid environment. The device (4) for electrically connecting the sensors located on the housing lid (1) to the control unit (3) in the housing shell (2) is embodied as a film conductor between the housing lid (1) and the sealing element (5) while the sealing element (5) is embodied as a plane sealing element.

Abstract: An arrangement is provided for detecting a shaft break on a rotor of a first turbine, especially a medium pressure turbine, of a gas turbine machine, especially an aircraft engine. A second turbine (11), especially a low pressure turbine, is positioned downstream from the first turbine. An actuating element (18) is positioned lying radially inwardly relative to a flow channel, between the rotor of the first turbine and a stator of the second turbine. A transmission element (22) is guided in the stator of the second turbine (11), in order to transmit a shaft break detected by the radially inwardly positioned actuating element (18) to a switching element (23) positioned radially outwardly relative to the flow channel on a housing (14) of the gas turbine.

Abstract: A static gas turbine component, especially for an aircraft engine, is formed at least partially region-wise of metal foam. An abradable shroud lining of metal foam and a carrier allow a radial through-flow of gas.

Abstract: An apparatus for removing harmful gas components out of the earth's atmosphere is a free-flying autonomous lightweight aircraft with an onboard gas processing system including gas separation or extraction devices, and inlets and outlets connected to the devices. Solar cells and/or thermoelectric generators provided on the craft produce electrical energy to operate the individual devices. The system may include a cryogenic closed-loop circulation system that participates in liquefying the extracted gas components. The apparatus is preferably a lighter-than-air craft like a dirigible. A method of extracting harmful gas components from the atmosphere involves flying the apparatus at a prescribed altitude level and operating the gas processing system to remove the harmful gas component from the atmosphere, then returning the apparatus to earth to offload the liquefied stored harmful gas component.

Abstract: In a method for production of a corrosion resistant and/or oxidation resistant coating, at least one metal of the platinum group or an alloy thereof is galvanically deposited onto a surface of a substrate, and thereafter the thusly galvanically coated substrate is aluminized. In a first stage of the galvanic deposition process a current magnitude applied for the galvanizing is increased continuously or step-wise beginning from an initial value up to a maximum value, and in a second stage of the galvanic deposition process the current magnitude applied for the galvanizing is maintained constant at the maximum value. The galvanic deposition of the or each metal of the platinum group or the corresponding alloy may be carried out using an open-celled or open-mesh or porous anode.

Abstract: The electric multiple conductor system (1) is used for the transmission of signals in differential mode, and has two signal lines (5, 6) and a shared reference line (7). Each signal line (5, 6) includes an attenuation or filter element (13, 14) with a connection branch (15, 16), which runs between a branch node (20, 21) in the respective signal line (5, 6) and the reference line (7). The attenuation or filter elements (13, 14) of the respective signal lines (5, 6) are nominally of the same size. Each connection branch (15, 16) respectively includes a serial connection of a first partial branch (17, 18) having a first reactive impedance (23, 24) and a second partial branch (19) having a second reactive impedance (25). The second partial branch (19) is a shared component of all attenuation or filter elements (13, 14). The multiple conductor system (1) achieves a very high level of common mode suppression.

Abstract: A device for producing water on board an aircraft includes at least one high temperature fuel cell entirely or partially integrated into a combustion chamber arrangement of a gas turbine aircraft engine. The combination of at least one fuel cell and a gas turbine engine is adapted to operate exclusively with hydrogen and atmospheric oxygen, and is embodied in an aircraft propulsion engine and/or an auxiliary power unit used for producing compressed air for a cabin and a power supply of the aircraft. The at least one high temperature fuel cell is fed with pure hydrogen on an anode side and with air on a cathode side. The combustion chambers of the turbine engine are fed with an air-hydrogen mixture, whereby at least the hydrogen supply can be regulated or completely shut off.

Abstract: There is provided a method of fabricating semiconductor devices that allows ion implantation to be performed at high temperature with ions accelerated with high energy to help to introduce dopant in a semiconductor substrate, in particular a SiC semiconductor substrate, at a selected region to sufficient depth. To achieve this the method includes the steps of: providing the semiconductor substrate at a surface thereof with a mask layer including a polyimide resin film, or a SiO2 film and a thin metal film; and introducing dopant ions.

Abstract: A gas turbine machine includes a second turbine (11), e.g. a low pressure turbine, positioned downstream from a first turbine (10), e.g. a medium pressure turbine. An arrangement for detecting a shaft break of a rotor shaft includes an operator element (16) positioned between the rotor of the first turbine (10) and a stator of the second turbine (11) radially inwardly relative to a flow channel, and a sensor element (21) guided in the stator of the second turbine (11), to convert a shaft break, detected by the radially inwardly positioned operator element (16), into an electrical signal and to transmit this electrical signal to a switching element which is positioned radially outwardly relative to the flow channel on a housing of the gas turbine machine.

Abstract: Two structural components, such as a gas turbine rotor hub and a rotor blade, are integrally joined to each other by friction welding, particularly linear friction welding. For this purpose, each component is provided with a joining surface and at least one of the two components is provided with a groove next to the respective joining surface. The groove extends fully or partly around the respective joining surface and serves for reducing stress in a normal and radial direction of the respective joining surface, whereby a more uniform heating of the joining zone is achieved and joining faults are avoided or at least reduced during the friction welding.

Abstract: A method and a clamping device for clamping a weft thread in a jet weaving machine are proposed. The weft thread strand runs through the beginning section (2.1) and the end section (2.2) of a mixing tube. The two sections between themselves form an engagement opening (8) and are connected with a first holding magnet (11) by a counter support (9). An actuator (6) in the form of an elastomeric bellows, which comprises a chamber (10), is located on the beginning section (2.1) of the mixing tube. The chamber (10) is connected to a valve (16) via a supply line (20) and is acted on variably with compressed air. By deformation of the actuator (6), a clamping element (7) connected thereto carries out a tilting movement between the counter support (9) and a contact stop part (19), which contains a second holding magnet (12). The holding magnets (11, 12) lead to an exact and reliable clamping of the weft thread (3).