Airbus Operations Gmbh

Christoph Winkelmann

Bernhard Schlipf

Christian Lorenz

Johannes Rupp

Jan Haserodt

Wilfried Ellmers

Benjamin Bishop

David Brakes

Stephen P Briancourt

Mark Heintjes

Martin Recksiek

Andreas Fleddermann

Michael Brady

Rico Weber

Ivan Petrov Ivanov

Martin Rechsiek

A wing for an aircraft is disclosed including a main wing and a trailing edge high lift assembly having a flap, and a connection assembly movably connecting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly includes a support element that is mounted to the flap and that is movably mounted to the main wing, such that the support element is movable relative to the main wing along a predefined path between a stowed position and a deployed position. The support element is formed as an elongate support beam that extends along a beam longitudinal axis between a front end and a rear end and has an intermediate portion between the front and rear ends.

Wing for an aircraft

An aircraft wing including a flap system mounted at a leading or trailing edge of the wing and includes at least two movable flap devices spaced apart in a spanwise direction Y from each other, each movable flap device supported by at least one support station and driven about a hinge axis by at least one drive system. The flap system includes a synchronizing torque element connected to the movable flap devices, wherein the synchronizing torque element is configured to transmit a torque between the movable flap devices to actuate a rotational movement of the movable flap devices, and wherein the synchronizing torque element is positioned between the movable flap devices and around an adjacent system or structural component that is also positioned between the movable flap devices.

Aircraft flap system

An actuator assembly for moving a movable aerodynamic surface of an aircraft is disclosed including an input section for introducing an externally provided rotary motion into the actuator assembly, and a geared rotary actuator having at least one actuator slice having a planetary gear with a sun gear couplable to the input section, a fixed gear attachable to a fixed component of the aircraft and an output gear couplable with the movable aerodynamic surface. At least one clutch is connected to the geared rotary actuator and is configured to couple the movable surface with the input section and to selectively decouple the movable surface from the input section, such that it is freely movable.

Actuator assembly for moving a movable wing tip of an aircraft

An equipment unit for installation in an aircraft includes an enclosure, in which at least one movable mechanical element is arranged, a supply duct, and a non-return valve, wherein the enclosure includes an inflow port and an outflow port, wherein the supply duct is connected to the inflow port, wherein the non-return valve is connected to the outflow port, wherein the supply duct is connectable to a source of heated air providable in the respective aircraft, and wherein the enclosure is designed that air supplied through the supply duct enters the enclosure through the inflow port, picks up moisture from inside the enclosure and exits through the outflow port.

Actively dried equipment unit with a movable mechanical element in an aircraft

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 wing for an aircraft is disclosed including a main wing, a leading edge high lift assembly having a leading edge high lift body, and a connection assembly movably connecting the leading edge high lift body to the main wing, wherein the connection assembly includes a drive system that is mounted to the main wing and connected to the leading edge high lift body for driving the leading edge high lift body between the retracted position and the extended position. The drive system includes a first drive unit and a second drive unit, the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section coupled to a first connection element and including a first output wheel. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section coupled to a second connection element and including a second output wheel.

To improve reliability and safety of an actuator assembly for a high-lift device, a torque sensing device is provided on a static structural part, which is used to mount the actuator of the actuator assembly to an aircraft interface, such as a rib or an interconnection strut. A controller determines a reaction torque value based on the output signal of the torque sensing device and monitors and controls the actuator based on the reaction torque value and predetermined load thresholds.

Actuator assembly for a high-lift device, wing assembly and aircraft equipped with such an actuator arrangement

A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

Wing arrangement for an aircraft

A wing () having a base section () and a tip section () pivotably connected to the base section () such that the tip section () is pivotable between a deployed position and a stowed position in which the spanwise length of the wing () is smaller than in the deployed position. The wing arrangement also has an actuating arrangement () including a linear hydraulic actuator () coupled between the base section () and the tip section () such that it is operable to selectively move the tip section () between the deployed position and the stowed position, a first and a second hydraulic connection portion () connected to the linear hydraulic actuator () such that they are in fluid communication with different chamber sections () of a cylinder () of the linear hydraulic actuator (), and a first hydraulic subsystem () and a second hydraulic subsystem ().

Foldable wing and actuator arrangement

A latching device for a wing including a support structure (), a latching bolt () having a longitudinal axis () and being slidably supported by the support structure () such that the latching bolt () is movable between a retracted position and an extended position. The latching device () includes a first hydraulic actuator () and a first connector assembly () adapted to be connected to a first hydraulic system of an aircraft (), and at least one second hydraulic actuator () and a second connector assembly () connected to a second hydraulic system. The first hydraulic actuator () and the second hydraulic actuator () are adapted to effect movement of the latching bolt () from the extended position into the retracted position independent of the other one of the at least one first hydraulic actuator () and the at least one second hydraulic actuator ().

Latching device for a foldable wing arrangement

A wing () having a fixed wing () and a wing tip device () rotatable between a flight configuration and a ground configuration, a rotational joint () rotatably couples the wing tip device () to the fixed wing () and a locking mechanism () locks the wing tip device () in the flight and ground configurations. The locking mechanism () includes first and second locking members () and first and second receiving members (), the locking mechanism () being configured to lock the wing tip device () in one of the flight configuration and ground configuration by receiving the first and second locking members () in the first and second receiving members () respectively, and to lock the wing tip device () in the other of the flight configuration and ground configuration by receiving the first locking member () in the second receiving member ().

Rotational joint for an aircraft folding wing

A wing () having a base section () and a tip section (), the base section () having a first end portion () and a second end portion (), the tip section () having a third end portion () and a fourth end portion (), wherein the second end portion () and the third end portion () are coupled so that the tip section () is pivotable with respect to the base section () about a pivot axis ('), and an actuating arrangement having an actuator () which is coupled to the base section () and the tip section () and which is operable to effect a pivotal movement of the tip section () relative to the base section () between a stowed position and a deployed position.

Foldable wing and actuating arrangement

A foldable wing for an aircraft includes a base wing having a base wing end region, a wing tip having a connection region, a first engagement means integrated into the base wing, a second engagement means integrated into the wing tip, and a drive mechanism coupled with the wing tip for moving the wing tip relative to the base wing. The first and second engagement means are adapted for engaging each other along a sliding course from a first position, in which the connection region of the wing tip and the base wing end region are in a flush contact to form a continuous wing, up to a second position, in which the first engagement means and the second engagement means disengage. The drive mechanism includes a first movement element and a second movement element at least partially extending in a spanwise direction, and supported in a linear guide each.

Foldable wing for an aircraft and aircraft having a foldable wing

A system for locking a foldable wing tip on a wing end of an aircraft includes at least one engagement device, at least one locking device comprising a support, a latch element rotatably held in the support and a lock element movably held on the support, a latch drive device coupled with the latch element of the at least one locking device for selectively rotating the latch element at least to an open position, a closed position and a test position, a lock drive device coupled with the lock element of the at least one locking device for selectively varying a distance of the lock element to the latch element between a neutral position and a locking position, wherein the support includes a receiving space extending into an insertion opening designed for receiving the engagement device. The latch element includes a circumferential surface section that selectively covers the insertion opening in an open position and uncovers the insertion opening in a closed position of the latch element. The latch element includes at least one locking recess arranged on a circumferential path of motion for engaging with the lock element in the closed position of the latch element and the locking position of the lock element. The rotatable latch element further includes at least one protrusion on the circumferential path of motion, which acts as a stop for the lock element. The system further includes a signaling device indicating a correct function when the lock element rests on the at least one protrusion.

System for locking a foldable wing tip on a wing end of an aircraft

The present disclosure provides an actuation system for a flight control surface of an aircraft, having: a support frame for supporting a flight control surface, the support frame being configured to be mounted to an airframe structure of the aircraft for movement between a first position and a second position to operate and move the control surface; an actuation mechanism configured to effect movement of the support frame between the second position and the first position; and a detection device for detecting a fault in the actuation mechanism, the detection device comprising a deflector configured to deflect or skew the support frame away from or out of the first position in the event of a fault in the actuation mechanism.

Growing community of inventors

Hamburg, Germany

Christoph Winkelmann