Airbus Operations Gmbh

Airbus Defence and Space Gmbh

Marc Hencke

Markus Gibbert

Bernhard Schlipf

Wolfgang Machunze

Atra Surya Gemilang

Benjamin Ehring

Florian Gehle

An aerodynamic system includes a support structure and an aerodynamic component movably coupled to the support structure via first and second coupling units such that the aerodynamic component can be moved relative to the support structure. The first and second coupling units can transfer a load from the aerodynamic component to the support structure. The system further includes an auxiliary coupling unit coupled between the aerodynamic component and the support structure, and configured to switch from a decoupling state to a coupling state, wherein, in the decoupling state, a load transfer via the at least one auxiliary coupling unit is prevented, and wherein, in the coupling state, a load transfer via the at least one auxiliary coupling unit is enabled.

Aerodynamic system for an aircraft

A wing () for an aircraft () including a main wing () and a high lift assembly () having a high lift body (), and a connection assembly () movably connecting the high lift body () to the main wing (), wherein the connection assembly () includes a first connection element () and a second connection element () movably mounted to the main wing () and mounted to the high lift body (), wherein the connection assembly () includes a first drive unit () drivingly coupled to the first connection element (), a second drive unit () drivingly coupled to the second connection element () and a third connection element () movably mounted to the main wing () and mounted to the high lift body (), the third connection element () is arranged between the first connection element () and the second connection element ().

Wing for an aircraft

A flap support for supporting a flap of a wing for an aircraft is disclosed and includes a load bearing fairing shell and a reinforcement structure at least partially received in the interior space of the fairing structure and mounted to the first and second side wall portions of the fairing shell. The fairing shell includes a front attachment device configured for attachment to a main wing, and the reinforcement structure includes an aft attachment device configured for attachment to the main wing. The flap support further includes a hinge device configured for forming an articulated connection to the flap.

Flap support for supporting a flap of a wing for an aircraft

A linkage mechanism for a flaperon includes a support structure linkage, a droop panel linkage, and a flaperon linkage. The support structure linkage is pivotally attached to a support structure of a wing of an aircraft. The droop panel linkage is pivotally attached a droop panel. The flaperon linkage is pivotally attached to a flaperon. A second end of the droop panel linkage and a second end of the flaperon linkage are pivotally attached to a connecting section of the support structure linkage. The connecting section is spaced apart from the pivot end of the support structure linkage such that the linkage mechanism transfers a pivoting motion from the flaperon into a pivoting motion of the droop panel.

Linkage mechanism for linking a flaperon to a droop panel of an aircraft

Disclosed herein is an exemplary embodiment of a system for driving a slat of an aircraft. The system includes first and second hinge support elements of a wing structure, a first arm device, a second arm device, and a third arm device. Also disclosed is an aircraft having the system, an aircraft wing having the system, and a method for driving a slat of an aircraft. The system utilizes a particular configuration of connection junctions, which rotatably connect the arm devices and the hinge support elements.

Growing community of inventors

Hamburg, Germany

Marc Hencke