Liebherr-Aerospace Lindenberg Gmbh

Bernd Schievelbusch

Manfred Fischer

Bernhard Hauber

Christian Trenkle

Werner Weiss

Stefan Hoechstoetter

Werner Mangler

Christoph Winkelmann

Josef Bär

Christian Kohlöffel

Susanne Conrad

Stefan Huth

Reinhold Kleinhans

Werner Dipl-Ing Weiss

Reinhold Dipl-Ing Kleinhans

Stefan Dipl-Ing Huth

Raphael Ladner

The present invention relates to an actuator system in an aircraft for monitoring a no-back brake, which system comprises an actuator for actuating a flap of a flight control system of the aircraft, a first torque sensor for detecting a torque on the drive side of the actuator, and a second torque sensor for detecting a torque on the output side of the actuator, wherein the actuator is provided with an auto-switching no-back brake to hold the flap actuated by the actuator in position. The actuator system further has a monitoring unit, which is connected to the first torque sensor and the second torque sensor and is designed to detect an acute or imminent fault condition of the no-back brake depending on an actuator state and the detected torque values of the first torque sensor and the second torque sensor.

Actuator system in an aircraft for monitoring a no-back brake

The invention relates to a flap system for an aircraft high lift system or an engine actuation with a rotary shaft system, one or more drive stations as well as elements for transmitting the drive energy from the rotary shaft system to the one or more drive stations, wherein at least one drive station includes at least two independent load paths with at least one rotational transmission each for actuating the flap kinematics, and per load path at least one mechanically coupling-free synchronization unit is provided for compensating regular load fluctuations between the load paths. The invention furthermore relates to a method for monitoring a flap system with at least two redundant load paths which each comprise at least one rotational transmission, wherein it is cyclically checked whether the difference of the output-side torques of the at least two load paths exceeds a defined threshold value and/or lies within a defined limit range.

Flap system for an aircraft high lift system or an engine actuation and method for monitoring a flap system

The present invention relates to a drive system for a variable camber aircraft wing having position variable front flaps and/or rear flaps, having drive shafts, which are arranged such that that the flaps undergo a change of position in operation of the drive shafts, and having one or more drive units in driving connection with the drive shafts, wherein at least one switchable coupling is provided via which the drive shafts of two flaps of an aircraft wing can be coupled to one another.

Drive system for a variable camber aircraft wing

A high-lift system of an aircraft has at least one drive unit, at least one load station as well as one or more transmissions for transmitting the drive energy of the drive unit to the at least one load station. One or more of the transmissions are made as transmission shafts from a material containing titanium or include a material containing titanium.

High-lift system of an aircraft

This invention relates to a device for monitoring the synchronism of one or more flaps of aircraft wings, wherein the device includes a control cable which is connected with the flaps such that the control cable follows the flap movement. In accordance with the invention, the path of installation of the control cable extends from a first point to a second point, one or both of which are arranged on non-movable structural components of the aircraft wing.

Device for monitoring the synchronism of flaps of an aircraft wing

The present disclosure relates to an aircraft high lift system with at least one load station for actuating a flap of a wing, preferably a landing flap and/or a leading-edge flap, at least one transmission with transmission portions located between branch transmissions, wherein by means of the branch transmissions actuating energy can be branched off from the transmission to the load station, and to a method for determining an operating condition of an aircraft high lift system.

Aircraft high lift system and method for determining an operating condition of an aircraft high lift system

The present invention relates to an aircraft high-lift system with at least one drive unit for operating the high-lift systems of the half wings (half-wing systems) and with at least one overload protection to avoid undesirably high operating torques in the half-wing systems, wherein the overload protection includes a comparator, by means of which the instantaneous values of the operating torques of the half-wing systems are compared and/or a condition caused by the difference of the operating torques is detected, and a limiter connected with the comparator, by means of which the drive unit is blocked, shut down or deactivated, and/or the torque of the drive unit is dissipated into the aircraft structure, when the difference of the operating torques determined in the comparator exceeds a limit value.

Aircraft highlift system

A device for detecting synchronous errors of high-lift surfaces such as landing flaps or slats on aircraft, having an optical conductor which is laid over at least two adjacent high-lift surfaces, a light source and an optical receiver which are allocated to different ends of the optical conductor, as well as an evaluation unit for determining a synchronous error of the high-lift surfaces on the basis of the light signal received from the optical receiver. The optical conductor is laid in such a way that the optical conductor experiences a break-free deformation due to synchronous errors and consequently causes a change of the transmitted light signals, and the evaluation unit compares the signal shape of the light signal received from the optical receiver or an optical receiver output signal derived therefrom with a nominal signal shape and determines the presence of a synchronous error on the basis of the deviation in shape between the received light signal or the optical receiver output signal derived therefrom and the nominal signal.

Device for detecting synchronous errors of high-lift surfaces on aircraft

The invention concerns an aircraft high-lift system with a drive system, components for transmitting the drive energy over the entire wing span to drive stations of individual segments of landing flap/slat flap systems, and with overload protection. According to the invention, the overload protection consists of electrical load sensors positioned at the drive-energy in-take points of the individual power trains on the flaps.

Aircraft high-lift system with overload protection

A device for the recognition of residual synchronization errors of multiple slats or flaps placed next to each other in an aircraft. The device includes a current carrying wire that runs through the slats or flaps. This wire is fastened at one end in the area of the gap between the slats or flaps and, on the other side, run through a cutting device. A detector can be used to detect and indicate the change in resistance when the wire is cut.

Growing community of inventors

Lindenberg, Germany

Bernd Schievelbusch