Airbus Operations Gmbh

Airbus (sas)

Liebherr-aerospace Lindenberg Gmbh

Andreas Fleddermann

Mark Heintjes

Martin Richter

Arnaud Didey

Christoph Winkelmann

Jan Haserodt

Alexandre Darbois

Jan-Arend Van Bruggen

Wolfgang Hartwig

Vincent Maire

Xavier Lamoussiere

Jan Arend Van Bruggen

Elko Van Balen

Christian Kohlöffel

Tobias Hartmann

A power control unit configured to supply hydraulic pressure and mechanical torque. To this end, the power control unit includes an electric motor coupled to a differential output transmission and a hydraulic pump. A switchable transmission device allows the torque of the motor to be redirected either to the output transmission, e.g., to drive high-lift devices, or to the hydraulic pump, e.g., to extend or retract landing gears.

Power control unit, hydraulic system and aircraft using the same

A drive system for driving a movable flow body having a drive unit, a shaft, a torque sensing device, a no-back friction unit, and an axial bearing. The drive unit is coupled with the shaft to rotate the shaft, the torque sensing device is coupled with at least one of the drive unit and the shaft to detect a torque transferred from the drive unit into the shaft, the no-back friction unit is arranged between the axial bearing and an axial support means of the shaft, such that an axial load of the shaft is supported by the axial bearing, and the no-back friction unit is configured to substantially not counteract a rotation of the shaft in a first direction of rotation of the shaft and to apply a friction-induced additional torque to the shaft in an opposite second direction of rotation.

Drive system with integrated torque sensing device

A method for testing a component in a high lift system of an aircraft comprises the steps of activating a brake coupled with at least one hydraulic motor, commanding a rotation of the at least one hydraulic motor for a predetermined period of time, wherein the brake remains activated, acquiring a sensor output of a motion sensor coupled with a central power control unit for moving a high lift surface during the commanded rotation of the at least one hydraulic motor, determining a motion of the power control unit from the acquired sensor output, comparing the determined motion with a predetermined threshold value, and generating a brake indication signal if the determined motion exceeds the predetermined motion threshold value.

Method for testing a component in a high lift system of an aircraft

A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components.

Method for generating hydraulic power in an aircraft, use of a hybrid power control unit and drive system

A fault-tolerant actuating system with at least one flap, adjustable on a respective wing of an aircraft, and with a control and monitoring device, includes: drive devices that are functionally connected to the control and monitoring device, with one of these drive devices in each case being associated with a flap, where each flap in each case is associated with a drive device, in each case including: two drive motors, two brake mechanisms, where each drive motor is associated with a brake mechanism for stopping rotation of the output of the respective drive motor, a differential that couples the outputs of the aforesaid to the aforesaid in a summing manner, an output shaft for coupling the output of the differential to drive connections, and a differential lock that is functionally connected to the control and monitoring device, which differential lock is coupled to the control and monitoring device in this manner, where each of the brake mechanisms as well as the differential lock can be operated by way of a command signal from the control and monitoring device; adjustment devices, that are coupled to the respective drive device associated with the flap, where each adjustment device in each case includes: a transmission gear unit, an adjustment mechanism and a position sensor that is functionally connected to the control and monitoring device for acquiring the adjustment state of the flap; where the control and monitoring device includes: an actuating function for generating command signals for the drive motors for adjusting the flap, a monitoring function by way of which a command signal is transmitted to both brake mechanisms and to the differential lock for operating the aforesaid when the control and monitoring device based on a comparison of sensor values of the position sensors on two different adjustment devices of a flap determines different adjustment states that exceed a predetermined extent, and a method for monitoring an actuating system.

Fault-tolerant actuating system for adjusting flaps of an aircraft, comprising adjustment kinematics with a fixed pivot, and a method for monitoring an actuating system

A method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device at least one high lift surface, which is actuated by means of a local mechanical final control element, is brought to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement. If a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit to the rotary shaft arrangement is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed.

Method and device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft

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Bremen, Germany

Andreas Fleddermann