Airbus Defence and Space Gmbh

Airbus Operations Gmbh

Eads Deutschland Gmbh

Markus Christmann

Mark Heintjes

Michael Hofmann

Alexander Naubert

Martin Recksiek

Christoph Giebeler

Bjoern Dorr

Ina Brueckner

Harald Rechter

Ina Ruckes

An aircraft includes an electromechanical actuator and a decoupling device. A form-fit between a drive element and a linkage point outside of the actuator element can be reversibly decoupled and recoupled. The decoupling device allows the actuator element to run freely in the event of a malfunction, which effectively prevents a jam.

Electromechanically controlled decoupling device for actuators

A reversible decoupling device is connected to an electromechanical actuator. The reversible decoupling device has an energy storage element configured to store the energy required for a decoupling in the decoupling device. The decoupling device can be re-coupled again after a completed test run so that the decoupling functionality can be easily tested.

Reversible decoupling device for actuators

A pneumatic decoupling device for an electromechanical actuator, in particular, for flight applications includes a pressure accumulator housing for storing a compressed gas, which can be released to a decoupling mechanism of an electromechanical actuator for separating the drive components, so that in the event of a decoupling the electromechanical actuator runs totally freely.

Pneumatically actuated decoupling device

A high lift system for an aircraft, which extends and retracts the landing flaps of the aircraft in a fully electric manner. In this context, a fully electric drive is used, comprising an electric motor having an internal redundancy, in such a way that the electric motor is configured as a fault-tolerant electric motor. It may thus be possible to do without a coupling gear unit in the electric motor.

High lift system for an aircraft

A detection and control device is provided for detecting a motor fault of an electric motor with star point topology, with an evaluation unit, a control unit, and a return unit. The return unit is configured for returning a star point potential of the electric motor to the evaluation unit, the evaluation unit is configured for evaluating the star point potential and the control unit is designed for passivating a motor fault on the basis of the evaluation. The function of the return unit and of the evaluation unit may also be assumed by control lines and by the control unit.

Fault detection method for electric motors with one or several star points

A method and a device for fault detection in the load path of a spindle actuator which is provided for actuating a high-lift flap of an aircraft, wherein the spindle actuator has a redundant load path which is formed by a spindle and a secondary connection which are connected rotationally fixedly to one another on the driven side and are coupled to the surface to be actuated and which are assigned separate load paths on the drive side, whereof the primary load path contains a primary spindle which is driven by a motor and can be fixed in its rotational movement by a primary brake, and the secondary load path contains the secondary inner connection, which is arranged concentrically in the primary spindle, which can be fixed in its rotational movement by a secondary brake, in which output signals representing the turning position of the spindle are detected and evaluated.

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Munich, Germany

Markus Christmann