Abstract: The present invention relates to an afterglow coating comprising a clear varnish and a photoluminescent pigment, wherein the pigment comprises a white luminous color in which the clear varnish is distributed. The present invention furthermore relates to methods for producing these coatings and to their use for coating surfaces in the cabin of aircraft.

Abstract: A fastening device for attaching a module element to a support structure in an aircraft includes a stud having a first end defining a broadened head configured to engage the support structure, a section which adjoins the head and defines a first lateral dimension and a second lateral dimension that is larger than, and is disposed at least substantially perpendicularly to, the first lateral dimension, and a second opposite end connected to a lever which is movable between open and closed positions relative to the stud. A bushing, which may be electrically conductive, is provided on and longitudinally movable along the stud, which is configured to contact the support structure and to support an outer wall of the module element. An eccentric may be actuated by the lever and is responsive to movement of the lever into the closed position to move the bushing along the stud towards the head.

Abstract: The present invention relates to a plug/socket arrangement, in particular an electrical and/or optical plug/socket arrangement of an aircraft or spacecraft, which comprises a housing and at least one insert which can be received in the housing. It further comprises a releasable connection means which is adjustable between a locked position, in which the insert and the housing are locked to one another, and an unlocked position, in which the insert and the housing are not locked to one another; and an adjustment member which is adjustable between an inoperative position, in which the adjustment member is not operatively connected to the connection means, and a release position, in which the adjustment member is operatively connected to the connection means for releasing the locked position into the unlocked position of the connection means.

Abstract: A display mount is provided for a vehicle, such an aircraft. The display mount includes, but is not limited to a support frame and a display accommodation device. The support frame is designed for incorporation in a supply channel, and the display accommodation device is designed to receive a display. The display accommodation device is connected to the support frame such that the display accommodation device is movable with a combined rotational movement and translational movement relative to the support frame between a first operating position and a second operating position.

Abstract: A fastening device for attaching a module element to a support structure in an aircraft includes a stud having a first end defining a broadened head configured to engage the support structure, a section which adjoins the head and defines a first lateral dimension and a second lateral dimension that is larger than, and is disposed at least substantially perpendicularly to, the first lateral dimension, and a second opposite end connected to a lever which is movable between open and closed positions relative to the stud. A bushing, which may be electrically conductive, is provided on and longitudinally movable along the stud, which is configured to contact the support structure and to support an outer wall of the module element. An eccentric may be actuated by the lever and is responsive to movement of the lever into the closed position to move the bushing along the stud towards the head.

Abstract: The invention relates to a method for underwater navigation, particularly for scuba divers, and for autonomous, manned, or remote-controlled underwater vessels, wherein the signals of at least one sensor, comprising at least one acceleration sensor for determining the actual position, are integratively analyzed, accuracy is improved by means of the use of reference measurements, and a correction is carried out by way of a correction vector obtained from the transformation of the vector of the accelerations measured by the acceleration sensor in the diving computer coordinate system into the global coordinate system, the comparison to at least one of the reference measurement values, the determination of the deviation and the reverse transformation of the deviation to the diving computer coordinate system.

Abstract: The present invention relates to a plug/socket arrangement, in particular an electrical and/or optical plug/socket arrangement of an aircraft or spacecraft, which comprises a housing and at least one insert which can be received in the housing. It further comprises a releasable connection means which is adjustable between a locked position, in which the insert and the housing are locked to one another, and an unlocked position, in which the insert and the housing are not locked to one another; and an adjustment member which is adjustable between an inoperative position, in which the adjustment member is not operatively connected to the connection means, and a release position, in which the adjustment member is operatively connected to the connection means for releasing the locked position into the unlocked position of the connection means.

Abstract: A display mount is provided for a vehicle, such an aircraft. The display mount includes, but is not limited to a support frame and a display accommodation device. The support frame is designed for incorporation in a supply channel, and the display accommodation device is designed to receive a display. The display accommodation device is connected to the support frame such that the display accommodation device is movable with a combined rotational movement and translational movement relative to the support frame between a first operating position and a second operating position.

Abstract: The present invention relates to an afterglow coating comprising a clear varnish and a photoluminescent pigment, wherein the pigment comprises a white luminous colour in which the clear varnish is distributed. The present invention furthermore relates to methods for producing these coatings and to their use for coating surfaces in the cabin of aircraft.

Abstract: A plug and a method for fixing at least two devices, includes a tension element, a pin, a lever element and a compression element. In one example, the tension element includes a tension stamp on a first end and a coupling member on a second end and a lever element includes a first sliding and a coupling element, with the pin coupling the lever element with the tension element. A compression element having an area-shaped contact that is capable of sliding onto the tension element until the area-shaped contact contacts the tension stamp. When the lever element is coupled to the tension element by a pin and is engaged by using a lever movement, a compression element is compressed by shortening a distance between the tension stamp and the lever element.

Abstract: The invention pertains to the projection of image contents in an aircraft. A mechanical projection surface is provided that features a gear with two thrust sleeves and two gear rods. The two thrust sleeves are displaced opposite to one another due to the rotation of a threaded rod. Each of the two thrust sleeves carries along an assigned gear rod such that a projection screen is respectively retracted or extended.

Abstract: A plug and a method for fixing at least two devices, includes a tension element, a pin, a lever element and a compression element. In one example, the tension element includes a tension stamp on a first end and a coupling member on a second end and a lever element includes a first sliding and a coupling element, with the pin coupling the lever element with the tension element. A compression element having an area-shaped contact that is capable of sliding onto the tension element until the area-shaped contact contacts the tension stamp. When the lever element is coupled to the tension element by a pin and is engaged by using a lever movement, a compression element is compressed by shortening a distance between the tension stamp and the lever element.

Abstract: A controller has two shunt lines connected in parallel with safety relays. For testing their switching capability, the safety relays are reversed to their idle positions and the change in voltage is monitored on their idle contacts. If voltage is missing, an error signal is issued. During the test, the parallel shunt line is closed so that the safety power line is not interrupted. Switching amplifiers having a response and action time which is a fraction of the preset response time of the safety relays control the safety relays. For testing the electrical control, the drives of the safety relays are switched to currentless and the change in voltage is monitored on the drives. If the change in voltage is inadequate, an error signal is issued. The safety relays remain in their operating positions during the test.

Abstract: A measuring instrument (11) for fill level sensors (4) having a measuring electrode (6) and a compensating electrode (9). The measuring instrument (11) has a bridge circuit whose one bridge branch (21) is formed by two series-connected test resistors (23, 24). The other bridge branch (22) is formed by the measuring resistor (17) on the measuring electrode (6) and the compensating resistor (18) on the compensating electrode (9). Between the two bridge branches (21, 22) a diagonal line (26) with a test switch (27) is provided. The measuring instrument (11) is controlled by the control circuit (13) so that the diagonal line (26) is closed outside of preset test time periods, and interrupted at preset test time periods. The end of the diagonal line (26) located between the two test resistors (23, 24) is connected to the base potential (25) of the measuring circuit (12).

Abstract: An electromagnetic actuator for actuating a gas-exchange valve in a reciprocating internal combustion engine, the electromagnetic actuator comprising: an armature which is operatively connected to the gas-exchange valve; two electromagnets, each having a pole face; two oppositely oriented restoring springs; wherein the armature is guided in a reciprocating manner counter to the force of the two oppositely oriented restoring springs between the pole faces of the two electromagnets whose current supply can be controlled by a control device, the two electromagnets being disposed in mutual spacing and acting as opening and closing devices; and at least one additional mass which is associated with the gas-exchange valve and can be guided so that it is movable relative thereto and in the same direction of the gas-exchange valve, the at least one additional mass entering into operative connection with the gas-exchange valve, in the final phase of the armature's motion in the direction of a respective one of the two

Abstract: A method of initiating motion of at least one of cylinder valve of a cylinder of a reciprocating engine, with each cylinder valve being actuated by an electromagnetic actuator having an electrical closing magnet and an electrical opening magnet, between which magnets an armature that is connected to the cylinder valve to be actuated is movably guided back and forth, counter to the forces of restoring springs, and with the alternating current supply to the closing magnet and the opening magnet being controlled by an electrical engine control. The natural frequency of the spring-mass system formed by the restoring springs and the armature with the cylinder valve is stored in the electrical engine control. The instantaneous rpm and position of the crankshaft with respect to a dead center point position and with reference to the stored natural frequency are detected by the engine control.

Abstract: A method is provided for reducing an impact speed of an armature on a pole face of an electromagnet in an electro-magnetic actuator, in which the armature moves toward the pole face against a restoring spring force when the coil of the electromagnet is charged with current. The method includes limiting a voltage applied to the coil to a predeterminable maximum value as the armature approaches the pole face so that a current flowing through the coil drops for a portion of the time of the voltage limitation.

Abstract: A method is provided for controlling an electromagnetic actuator having an electromagnet including a magnetic core presenting a pole face and an electromagnet coil wound around the magnetic core, a return spring and an armature connected to an actuation mechanism and movable toward the pole face by a magnetic force of the electromagnet against the force of the return spring. The method includes: detecting a time behavior and/or value of current and/or voltage present at the electromagnet coil during a time period when the armature does not move relative to the electromagnet, and deriving a value corresponding to the actual ohmic resistance and/or inductance of the electromagnet coil from the detected time behavior and/or value from the detecting step for compensating changes in the ohmic resistance of the electromagnet coil.

Abstract: A method for a controlling cylinder valve drive in a piston-type internal combustion engine includes the steps of detecting vibration signals generated during operation by the cylinder valve drive or the cylinder valve, and actuating the cylinder valve drive in dependence on a value of the detected vibration signals which corresponds to the impact time or impact speed of the cylinder valves.

Abstract: A method is provided for monitoring a cylinder valve which is actuated by an electromagnetic actuator including an electromagnet having a magnetic core presenting a pole face and a coil wound around the magnetic core, a return spring and an armature that can be moved by the electromagnet in a direction toward the pole face counter to a force of the return spring for acting upon the cylinder valve.