Abstract: Closures with a tamper evidence feature that is reshaped to connect it to the container neck are disclosed. Methods and systems for carrying out the methods, and to mold stacks for making the closures are also disclosed. The tamper evidence feature can be a band, a portion of a cylindrical skirt or a panel formed in the cylindrical skirt.

Abstract: Closures with a tamper evidence feature that is reshaped to connect it to the container neck are disclosed. Methods and systems for carrying out the methods, and to mold stacks for making the closures are also disclosed. The tamper evidence feature can be a band, a portion of a cylindrical skirt or a panel formed in the cylindrical skirt.

Abstract: Closures with a tamper evidence feature that is reshaped to connect it to the container neck are disclosed. Methods and systems for carrying out the methods, and to mold stacks for making the closures are also disclosed. The tamper evidence feature can be a band, a portion of a cylindrical skirt or a panel formed in the cylindrical skirt.

Abstract: Closures with a tamper evidence feature that is reshaped to connect it to the container neck are disclosed. Methods and systems for carrying out the methods, and to mold stacks for making the closures are also disclosed. The tamper evidence feature can be a band, a portion of a cylindrical skirt or a panel formed in the cylindrical skirt.

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.

Abstract: A contact blade for a plug-in connector part includes oppositely situated first and second contact arms extending longitudinally. The first contact arm has a primary opening dividing the first contact arm into first and second contact webs on respective sides of the primary opening. The first contact web has a contact opening dividing the first contact web into inner and outer contact skids on respective sides of the contact opening. The inner contact skid is between the contact opening and the primary opening and the outer contact skid is between the contact opening and an edge of the first contact arm. The contact opening has a transverse bulge extending laterally toward the primary opening such that the outer contact skid has a widened section next to the transverse bulge. A contact point, for contacting a plug pin, is on the widened section of the outer contact skid.

Abstract: A contact blade for a plug-in connector part includes oppositely situated first and second contact arms extending longitudinally. The first contact arm has a primary opening dividing the first contact arm into first and second contact webs on respective sides of the primary opening. The first contact web has a contact opening dividing the first contact web into inner and outer contact skids on respective sides of the contact opening. The inner contact skid is between the contact opening and the primary opening and the outer contact skid is between the contact opening and an edge of the first contact arm. The contact opening has a transverse bulge extending laterally toward the primary opening such that the outer contact skid has a widened section next to the transverse bulge. A contact point, for contacting a plug pin, is on the widened section of the outer contact skid.

Abstract: An air-conditioning system for an aircraft has a fresh air line, a recirculation device, an air-mixing device, an air distribution system with multiple cabin air outlets, and a control unit. The control unit is designed to determine or to receive flight-specific parameters characterizing the flight state of the aircraft, and to determine or to receive environment-specific parameters which characterize an air quality in the environment of the aircraft. A first operating state of the air-conditioning system is brought about in the case of a predefined limit value of at least one environment-specific parameter being exceeded, and a second operating state of said system is brought about during a second flight state, which is outside the first flight state. In the second operating state, the fresh air line is fluidically connected to the air-mixing device, and in the first operating state, the fresh air line is separated from the air-mixing device.