Airbus Operations Gmbh

Airbus Deutschland Gmbh

Eads Deutschland Gmbh

Deutsches Zentrum Fur Luft-und Raumfahrt E.v.

Deutsches Zentrum Fuer Luft-und Raumfahrt E.v

Christoph Giebeler

Martin Recksiek

Markus Christmann

Ina Brueckner

Mark Heintjes

Bjoern Dorr

Harald Rechter

Ina Ruckes

Ina Brückner

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 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.

Method and device for fault detection in the load path of a spindle actuator

A landing flap drive system, in one example, includes a first drive motor for operating a landing flap. In this arrangement, the landing flap drive system is integrated in a track of the landing flap such that final assembly and integration of the system are facilitated to a significant extent.

Landing flap drive system

A method and a device for redundantly supplying several electric servomotors or drive motors by a common power electronics unit, particularly in an aircraft, wherein the power electronics unit contains a number of electronic motor control units, and wherein the electric motors are operated with nominal power if the electronic motor control units are fully functional. The motors are operated with the available residual power of the motor control units if partial failure of the motor control units occurs. The motors may be operated sequentially or simultaneously.

Method and device for redundantly supplying several electric servomotors or drive motors by means of a common power electronics unit

Growing community of inventors

Bremen, Germany

Christoph Giebeler