Airbus Operations Gmbh

Koninklijke Philips Corporation N.v.

U.S. Philips Corporation

Christian Lorenz

Michael Grass

Benjamin Bishop

Juergen Weese

Thomas Buelow

Jochen Peters

Jens Von Berg

Robert Manzke

Christian Buerger

Christoph Winkelmann

Olivier Ecabert

Jan Haserodt

Wilfried Ellmers

J&uuml;rgen Weese

Rico Weber

Ivan Petrov Ivanov

A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion and a flight latch device for latching the foldable wing tip portion in the extended position, wherein the flight latch device includes a housing, a latch bolt, and a motor for driving the latch bolt between the latched and unlatched positions. A flight latch device includes a threaded shaft rotationally driven by the motor, a nut engaging the shaft, so that the nut can rotate relative to the shaft, the nut is connected to the housing via a linear guide and is connected to the latch bolt for common linear movement with the latch bolt, and the flight latch device includes an offset compensation, providing that the shaft is supported pivotable relative to the housing and the latch bolt is coupled to the nut via a compensational bearing allowing angular play between the nut and the latch bolt.

Wing for an aircraft

A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position, and an actuation unit for actuating the foldable wing tip portion for movement about the hinge axis. The wing includes a brake unit for securing the foldable wing tip portion in the folded position, and the brake unit is formed separately from the actuation unit.

An actuation unit for actuating a foldable wing tip portion of a wing for an aircraft is disclosed including a motor configured to be mounted to a fixed wing for an aircraft, a drive pinion driven rotationally by the motor, a first rack configured to be mounted to the fixed wing, a second rack configured to be mounted to the foldable wing tip portion, a third rack configured to be mounted to the fixed wing movably along a defined first movement path and drivingly engaged by the drive pinion, and a transfer pinion mounted to the third rack rotatably about an axis of rotation extending perpendicular to the first movement path.

Actuation unit for actuating a foldable wing tip portion of a wing for an aircraft

A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion, and a flight latch device for latching the foldable wing tip portion in the extended position, wherein the flight latch device includes a housing, a latch bolt linearly movable relative to the housing, and a motor for driving the latch bolt. The flight latch device includes a threaded shaft having an external thread and being mounted to the housing in a torque proof manner, the flight latch device includes a nut having an internal thread engaging the external thread of the shaft, so that the nut can rotate about the shaft along the external thread.

A wing for an aircraft, comprising a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatably about a first hinge axis between an extended and folded positions, and an actuation unit to actuate the foldable wing tip portion for movement about the first hinge axis. The actuation unit comprises a link, a first and a second linear actuator. The link is rotatably mounted to the fixed wing via a second hinge, the first linear actuator is rotatably mounted to the fixed wing via a third hinge spaced from the second hinge, and is rotatably mounted to the link via a fourth hinge spaced from the second hinge. The second linear actuator is rotatably mounted to the foldable wing tip portion via a fifth hinge, and is rotatably mounted to the link via a sixth hinge spaced from the second hinge.

An actuation unit () for actuating a foldable wing tip portion () of a wing () for an aircraft (). The actuation unit () includes a track () configured to be mounted to a fixed wing (), a carriage () configured to engage the track () for guided movement along the track (), and configured to be coupled to a drive unit () for driving the carriage () along the track (), and a link () configured to be coupled to the carriage () and configured to be coupled to a foldable wing tip portion ().

A wing () for an aircraft () including a fixed wing (), a foldable wing tip portion () mounted to the fixed wing () via a first hinge () rotatable about a first hinge axis () between an extended position () and a folded position (), and an actuation unit () arranged at the fixed wing () and coupled to the foldable wing tip portion () via a linkage () including a first link element () and a second link element (), wherein the first link element () is mounted to a rotatable output () of the actuation unit () and is rotatably coupled to the second link element () via a second hinge (), and wherein the second link element () is rotatably coupled to the foldable wing tip portion () via a third hinge ().

A latching device for a wing () including a base () and a tip section (). There is a first bore () extending from the base section () and a second bore () extending from the tip section () wherein the bores are aligned when the tip section is deployed for flight and out of alignment when the tip section () is folded. The latching device () includes a housing () with an interior cavity (), a spindle () in the interior cavity, a nut () threaded on the spindle, wherein rotation of the spindle causes; a latching bolt () coupled to the nut () and being moved as the nut moves along the rotating spindle between retracted and extended positions; a guide () to guide the nut () along the spindle and of the latching bolt between the retracted position and the extended position, and a latch actuator ().

Latching device for a wing arrangement for an aircraft

A wing for an aircraft is disclosed having a fixed wing and a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position. The wing may include an actuation unit with reduced complexity, and may include a ground latch device for latching the foldable wing tip portion in the folded position.

An actuation unit () for actuating a foldable wing tip portion () includes a first housing part () including a first attachment device () configured for attachment to a fixed wing (), and a second housing part () including a second attachment device () configured for attachment to a foldable wing tip portion (). The second housing part () is rotatable about a main axis of rotation (). The second housing part () includes a toothed rack () having a concave shape and facing the main axis of rotation (). A drive pinion () is supported at the first housing part () and engaging the toothed rack () for driving the second housing part () rotatingly relative to the first housing part (). The drive pinion () is driven by a coupling arrangement () that is configured to be coupled to an output () of a motor unit ().

A wing for an aircraft is disclosed having a fixed wing, and a foldable wing tip portion mounted to the fixed wing via a tip hinge rotatable about a tip hinge axis between an extended position and a folded position. An arresting device is provided that allows to arrest the foldable wing tip portion with respect to the fixed wing in a very precise position and at the same time can be engaged in a simple and quick manner, is achieved in that the wing includes an arresting system including a first hook mounted to the foldable wing tip portion and a second hook mounted to the fixed wing, wherein the first hook and the second hook are configured to be moved relative to one another between an arrested position, where the first and second hooks are engaged and relative movement of the first and second aircraft components is inhibited, and a release position, where the first and second hooks are disengaged and relative movement of the first and second aircraft components is allowed.

Arresting system for arresting a first aircraft component relative to a second aircraft component

A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatable about a first hinge axis between an extended position and a folded position, and an actuation unit for actuating the foldable wing tip portion for movement about the first hinge axis. A wing having an actuation unit with reduced complexity and weight and that is arranged entirely inside the outer contour of the wing is disclosed in which the actuation unit is arranged at one of the fixed wing and the foldable wing tip portion and is coupled to the other of the fixed wing and the foldable wing tip portion via a linkage. The linkage includes a first link element and a second link element, wherein the first link element is rotatably mounted to the one of the fixed wing and the foldable wing tip portion via a second hinge and is rotatably coupled to the second link element via a third hinge.

A wing for an aircraft having a fixed wing, a foldable wing tip portion rotatably attached to the fixed wing and an actuation unit for rotating the foldable wing tip portion relative to the fixed wing about a hinge axis is disclosed. The actuation unit includes a traction means for transmitting traction between the fixed wing and the foldable wing tip portion, a main wheel attached to the foldable wing tip portion and in contact with the traction means and a drive means for generating traction to be transmitted by the traction means. The actuation unit generates traction with the drive means in the traction means so that the foldable wing tip portion can be rotated relative to the fixed wing.

The present invention relates to a device () for determining an optimal placement of a pedicle screw (), comprising a processing unit (), wherein the processing unit is configured to receive a model data set representing a model surface () of a human vertebra model () and a pedicle screw model () being optimally placed in a span of a pedicle section () of the model surface, wherein the processing unit is configured to receive 5 image data representing a surface image () of at least one human vertebra (), GO and wherein the processing unit is configured to adapt the model data set for each of a number of the at least one human vertebra, such that an adapted model data set representing a correspondingly adapted model surface (), which fits to the surface image of the respective human vertebra, is provided for each of the number of the at least one human vertebra, wherein each of the 10 adapted model data sets also represents a correspondingly adapted pedicle screw model (). The present invention further relates to a corresponding method, a corresponding computer program element and a corresponding computer readable medium.

Determining an optimal placement of a pedicle screw

A wing arrangement for an aircraft including a latching arrangement (&#x2033;) having a latching member (&#x2033;) and an engagement device (), wherein the latching member (&#x2033;) is fixed to a wing tip section (), and the engagement device () has a base member () on a wing base section () and has an abutment surface (), and an engagement member () supported on the base section () and moves between a release position and a latching position by an actuator (') coupled to the engagement member () and the base section (), wherein when the tip section () is in the deployed position, the latching member (&#x2033;) abuts the abutment surface () and the engagement member () can move between the release position and the latching position, wherein when the latching member (&#x2033;) abuts the abutment surface () and the engagement member () is in the latching position, the engagement member () abuts on a surface section of the latching member (&#x2033;) facing away from the abutment surface () to prevent a pivot movement of the tip section.

Growing community of inventors

Hamburg, Germany

Christian Lorenz