Abstract: A system for detecting overpressure in an aircraft including a door with a door frame and a door leaf with a first and second door leaf face. The door is mountable in an aircraft where the first door leaf face faces the interior and the second door leaf face faces the surroundings of the aircraft. The door leaf is movably attached to the door frame and selectively movable between an opened position where a door opening defined by the door frame is accessible and a closed position where the door leaf closes off the door opening. The door has a pair of contact faces including a first contact face on the door leaf and a second contact face on the door frame.

Abstract: A differential pressure sensor system for use in an aircraft comprises a differential pressure sensor for determining a differential pressure between a pressurizable aircraft cabin and an aircraft environment, the differential pressure sensor having a first port connectable to the pressurizable aircraft cabin via a first line and a second port connectable to the aircraft environment via a second line. A shut-off device of the differential pressure sensor system is arranged in the second line which is switchable between an open position in which it opens the second line, such that a pressure prevailing in the aircraft environment acts on the second port of the differential pressure sensor, and a shut-off position in which it closes the second line, such that the second port of the differential pressure sensor is shut off from the pressure prevailing in the aircraft environment.

Abstract: A device providing a signal indicating whether a deployed aircraft evacuation slide is ready for use. A tilt sensor measures tilt angle about a predetermined axis and a tilt sensor measurement signal is provided. An inertial sensor detects acceleration and provides an inertial sensor measurement signal. A slide signal input terminal receives a slide signal indicating deployment of an evacuation slide and of a deployment length. A tilt angle signal output terminal at which a tilt angle signal is provided, and a slide status output terminal and a control unit to determine, based on the detected acceleration, a moment when the device is at rest with respect to earth and to set orientation of the reference plane to a predetermined orientation. The control unit stores data depending on position of a door, and can determine a slide length. A slide status signal is provided at the slide status output terminal.

Abstract: A system for detecting overpressure in an aircraft including a door with a door frame and a door leaf with a first and second door leaf face. The door is mountable in an aircraft where the first door leaf face faces the interior and the second door leaf face faces the surroundings of the aircraft. The door leaf is movably attached to the door frame and selectively movable between an opened position where a door opening defined by the door frame is accessible and a closed position where the door leaf closes off the door opening. The door has a pair of contact faces including a first contact face on the door leaf and a second contact face on the door frame.

Abstract: A system to detect a pressure difference between the interior of a cabin of an aircraft and the exterior of the aircraft. The system includes a window arrangement having a first windowpane with a first surface and an opposite second surface and is adapted to be mounted in an aircraft such that the first surface of the first windowpane faces the exterior of the aircraft and is subjected to ambient outside atmospheric pressure and the second surface faces the cabin interior, and a pressure sensor including a first pressure port. The first windowpane includes a first air passage opening extending between the first and second surfaces of the first windowpane, and the pressure sensor is sealingly connected to the first air passage opening such that the first pressure port of the pressure sensor is subjected to pressure acting on the first surface of the first windowpane.

Abstract: A differential pressure sensor system for use in an aircraft comprises a differential pressure sensor for determining a differential pressure between a pressurizable aircraft cabin and an aircraft environment, the differential pressure sensor having a first port connectable to the pressurizable aircraft cabin via a first line and a second port connectable to the aircraft environment via a second line. A shut-off device of the differential pressure sensor system is arranged in the second line which is switchable between an open position in which it opens the second line, such that a pressure prevailing in the aircraft environment acts on the second port of the differential pressure sensor, and a shut-off position in which it closes the second line, such that the second port of the differential pressure sensor is shut off from the pressure prevailing in the aircraft environment.

Abstract: An interface unit for use in updating software of an aircraft component on board an aircraft. The interface unit comprises a first interface to connect to a server providing one or more software updates for upload to the aircraft component, and a second interface to connect to the aircraft component. The interface unit further comprises a receiving component configured to receive a software update from the server via the first interface for upload to the aircraft component, and an uploading component configured to upload the received software update to the aircraft component via the second interface.

Abstract: A device providing a signal indicating whether a deployed aircraft evacuation slide is ready for use. A tilt sensor measures tilt angle about a predetermined axis and a tilt sensor measurement signal is provided. An inertial sensor detects acceleration and provides an inertial sensor measurement signal. A slide signal input terminal receives a slide signal indicating deployment of an evacuation slide and of a deployment length. A tilt angle signal output terminal at which a tilt angle signal is provided, and a slide status output terminal and a control unit to determine, based on the detected acceleration, a moment when the device is at rest with respect to earth and to set orientation of the reference plane to a predetermined orientation. The control unit stores data depending on position of a door, and can determine a slide length. A slide status signal is provided at the slide status output terminal.

Abstract: A fire protection trolley for securing a burning or flammable article, in particular for the interior of an aircraft or spacecraft, includes a sealable, fire-resistant safety container, and an interface connected to the safety container and formed for connection to a counterpart interface of a smoke gas exhaust line for removing a medium located in the safety container. A fire protection device has a fire protection trolley of this type which may be included in an aircraft or spacecraft.

Abstract: A system to detect a pressure difference between the interior of a cabin of an aircraft and the exterior of the aircraft. The system includes a window arrangement having a first windowpane with a first surface and an opposite second surface and is adapted to be mounted in an aircraft such that the first surface of the first windowpane faces the exterior of the aircraft and is subjected to ambient outside atmospheric pressure and the second surface faces the cabin interior, and a pressure sensor including a first pressure port. The first windowpane includes a first air passage opening extending between the first and second surfaces of the first windowpane, and the pressure sensor is sealingly connected to the first air passage opening such that the first pressure port of the pressure sensor is subjected to pressure acting on the first surface of the first windowpane.

Abstract: A door system for an aircraft or spacecraft having a door and an actuator for actuating the door. The actuator includes an actuator drive which moves the door in relation to the aircraft or spacecraft, a detection device which determines movement information of the door and/or of the actuator, an actuator control unit which controls the actuator based on the movement information, and an actuator housing which surrounds the actuator drive and the actuator control unit.

Abstract: A fire protection trolley for securing a burning or flammable article, in particular for the interior of an aircraft or spacecraft, includes a sealable, fire-resistant safety container, and an interface connected to the safety container and formed for connection to a counterpart interface of a smoke gas exhaust line for removing a medium located in the safety container. A fire protection device has a fire protection trolley of this type which may be included in an aircraft or spacecraft.

Abstract: A door system for an aircraft or spacecraft having a door and an actuator for actuating the door. The actuator includes an actuator drive which moves the door in relation to the aircraft or spacecraft, a detection device which determines movement information of the door and/or of the actuator, an actuator control unit which controls the actuator based on the movement information, and an actuator housing which surrounds the actuator drive and the actuator control unit.

Abstract: The present invention provides a device for providing an aircraft flight status signal which indicates whether the aircraft is in the air or on the ground, which device calculates the flight status signal as a function of a number of differently provided flight speed signals, a number of differently provided engine status signals, a number of differently provided evacuation signals, a number of differently provided front undercarriage status signals and a number of differently provided main undercarriage status signals.

Abstract: The present invention provides a device for providing an aircraft flight status signal which indicates whether the aircraft is in the air or on the ground, which device calculates the flight status signal as a function of a number of differently provided flight speed signals, a number of differently provided engine status signals, a number of differently provided evacuation signals, a number of differently provided front undercarriage status signals and a number of differently provided main undercarriage status signals.