Abstract: A sputtering target is produced by powder metallurgy. The sputtering target is formed of tungsten (W), nickel (Ni) and one further metal X selected from group 5 or group 6 of the periodic table of elements, as well as inevitable impurities. The sputtering target has a two-phase microstructure, wherein one phase is pure W and the other phase is a mixed phase selected from the group of NiWX, NiW, NiX and mixtures thereof. There is also described a process for producing a WNiX sputtering target via the powder-metallurgical route.

Abstract: A drive system (1) for an aircraft (50), including a first drive unit (11) which has a first power generator (21) for delivering first electrical power (P1) and a first propulsion unit (31) which is connected to the first power generator (21) to generate propulsion from the first electrical power (P1), and a second drive unit (12) which has a second power generator (22) for delivering second electrical power (P2) and a second propulsion unit (32) which is connected to the second power generator (22) to generate propulsion from the second electrical power (P2), and an interconnection device (40) which is configured to interconnect the first propulsion unit (31) or the first power generator (21) with the second drive unit (12) to supply power in the event of a fault condition of the first drive unit (11).

Abstract: The invention pertains to a fuel system for supplying an aircraft with hydrogen. The fuel system comprises a first inner tank and a separate, second inner tank, each for storing hydrogen, and an outer tank, which surrounds the inner tanks. The first inner tank and the second inner tank separately from each other are fluidically connected to at least one first supply device for supplying the aircraft with hydrogen. The invention further pertains to an aircraft with a fuel system, and a method.

Abstract: An ejector jet pump for a recirculation system of a fuel cell drive for humidifying and recirculating hydrogen in the fuel cell system, with at least one fuel cell, including a water separator for separating water and forming droplet-free gas from the moist exhaust gas of the fuel cell, and a gas delivery device arranged downstream of the water separator, wherein the water separator has a suction connection for feeding the exhaust gas into the water separator, wherein the water separator has a water outlet for discharging water separated from the moist exhaust gas, wherein the water separator has a droplet-free gas connection which opens into the gas delivery device. The water separator between the suction connection and the gas delivery device can be be tubular in shape and have a bend at an angle ?. of at least 60°and at most 120°.

Abstract: A power supply system (1) for a propulsion system (40) of an aircraft (50), including a first heat source (11) in the form of a fuel cell unit (21), a second heat source (12), and a heat exchanger (13). The first and second heat sources (11, 12) and the heat exchanger (13) are connected to one another in a cooling circuit (14) for conducting a cooling fluid (16). The first heat source (11) has a first optimal operating temperature Topt_1 and the second heat source (12) has a second optimal operating temperature Topt_2. The first optimal operating temperature Topt_1 is greater than the second optimal operating temperature Topt_2 (Topt_1>Topt_2). A recirculation circuit (19) is associated with the first heat source (11) in the cooling circuit (14), via which cooling fluid (16) already utilized during operation for cooling the first heat source (11) is reusable for cooling the first heat source (11) before passing through the heat exchanger (13). The heat exchanger (13) includes an actuatable inlet (13.1).

Abstract: The invention is directed to an aircraft having a fuel-cell propulsion system that includes a fuel cell for supplying electricity to an electric propulsion apparatus of the aircraft, a fuel store for storing fuel for the fuel cell, and a cooling apparatus for cooling the fuel cell. A main heat exchanger of the cooling apparatus and the fuel store are arranged on a top side of a fuselage of the aircraft, and the main heat exchanger is arranged in front of the fuel store toward the aircraft nose.

Abstract: An electrical plug connector includes a plug connector housing and a connecting lever. The connecting lever is rotatable with respect to the plug connector housing between an initial position and an end position. The connecting lever includes a locking element having a first part fixed to the connecting lever and a second part displaceable relative to the first part. The locking element mechanically locks the connecting lever in the end position to the plug connector housing when the connecting lever is in the end position and the second part is displaced relative to the first part to a locking position. The first and second parts of the locking element respectively carry first and second sections of an optical code. The optical code is completed when the second part is displaced relative to the first part to the locking position whereby the optical code is detectable by an optical reading device.

Abstract: The invention relates to a holder (10) with a securing means (1) for releasably securing a hand-held torch (5), the securing means (1) having at least in regions a negative form (2) of the hand-held torch (5) for reproducibly positioning the hand-held torch (5) in the holder (10), and the securing means (1) being adapted, at least in regions, to the outer contour (3) of the hand-held torch (5) when the hand-held torch (5) is secured. The invention further relates a hand-held torch (5) having a holder (10).

Abstract: An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

Abstract: An electric generator including a number of electric accumulators and at least one heat-sink device using a phase-change material configured to pick up the excessive thermal energy produced by one of the electric accumulators and change phase in order to absorb a large quantity of thermal energy in the form of latent heat.

Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

Abstract: A multipole electrical plug-in connector includes a plug-in connector housing and a mounting block. The plug-in connector housing has a housing base that extends perpendicular to a longitudinal axis of the plug-in connector housing. The housing base has insertion openings. Contact elements are respectively inserted through the housing base insertion openings. Each contact element has a contact portion that is connectable to a mating plug-in connector, a press-in portion, with a fir tree profile, that is pressed into the housing base insertion opening in which the contact element is inserted through, and a connection portion for connecting an electrical connection line. Each contact element further has a retaining portion between the press-in portion and the connection portion. The retaining portions of the contact elements are inter-lockingly fastened in the mounting block. A method for producing a multipole electrical plug-in connector of this type is provided.

Abstract: An electrical plug connector includes a plug connector housing and a connecting lever. The connecting lever is rotatable with respect to the plug connector housing between an initial position and an end position. The connecting lever includes a locking element having a first part fixed to the connecting lever and a second part displaceable relative to the first part. The locking element mechanically locks the connecting lever in the end position to the plug connector housing when the connecting lever is in the end position and the second part is displaced relative to the first part to a locking position. The first and second parts of the locking element respectively carry first and second sections of an optical code. The optical code is completed when the second part is displaced relative to the first part to the locking position whereby the optical code is detectable by an optical reading device.

Abstract: A process for producing a W—Ni sputtering target includes providing the sputtering target with 45 to 75 wt % W and a remainder of Ni and common impurities. The sputtering target contains a Ni(W) phase, a W phase and no or less than 10% by area on average of intermetallic phases measured at a target material cross section.

Abstract: An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

Abstract: An electric generator including a number of electric accumulators and at least one heat-sink device using a phase-change material configured to pick up the excessive thermal energy produced by one of the electric accumulators and change phase in order to absorb a large quantity of thermal energy in the form of latent heat.

Abstract: A multipole electrical plug-in connector includes a plug-in connector housing and a mounting block. The plug-in connector housing has a housing base that extends perpendicular to a longitudinal axis of the plug-in connector housing. The housing base has insertion openings. Contact elements are respectively inserted through the housing base insertion openings. Each contact element has a contact portion that is connectable to a mating plug-in connector, a press-in portion, with a fir tree profile, that is pressed into the housing base insertion opening in which the contact element is inserted through, and a connection portion for connecting an electrical connection line. Each contact element further has a retaining portion between the press-in portion and the connection portion. The retaining portions of the contact elements are inter-lockingly fastened in the mounting block. A method for producing a multipole electrical plug-in connector of this type is provided.

Abstract: A process for producing a W—Ni sputtering target includes providing the sputtering target with 45 to 75 wt % W and a remainder of Ni and common impurities. The sputtering target contains a Ni(W) phase, a W phase and no or less than 10% by area on average of intermetallic phases measured at a target material cross section.

Abstract: A mixing device that is particularly suitable for use in an aircraft air-conditioning system comprising a cold air supply line adapted to supply cold air to the mixing device. A first recirculation air supply line is adapted to supply recirculation air to the mixing device. A mixing chamber is connected to the cold air supply line and the first recirculation air supply line and is adapted to supply the cold air supplied to the mixing device via the cold air supply line with the recirculation air supplied to the mixing device via the first recirculation air supply line. The first recirculation air supply line has a heat transfer portion which is thermoconductively connected to an area of a wall delimiting the mixing chamber that is at risk of icing.