Airbus Operations Gmbh

Airbus Deutschland Gmbh

Eads Deutschland Gmbh

Xavier Hue

Bernhard Schlipf

Tamas Havar

Franz Stadler

Marco Goettinger

Mark Heintjes

Luc Andreani

Christopher Payne

Llifon Williams

Simon W Topping

Martin Mayneord

David Belfourd

Morten Raudszus

Simon Topping

A method for producing a load introducing element for a control surface of an aircraft or a spacecraft, includes cutting to size preformed fibrous substructures out of a fibrous material. The method also includes draping the fibrous substructures to mold at least one first component, at least one second component and at least one first flange in the form of a single semi-finished product. Further, the method includes inserting the semi-finished product into a mold, injecting matrix material, and curing the semi-finished product to form a finished product.

Method for producing a load introducing element

A high lift system for an aircraft includes a basic body, a flap which is movably mounted on the basic body and has a flap edge, and a retaining element. The high lift system is set up to form a gap between the flap edge and the basic body. The retaining element is mounted on a region of the flap close to the flap edge and extends towards the basic body to restrict the distance between the flap edge and the basic body. The retaining element is preferably configured as a linear attachment means. Consequently, a gap dimension between a flap and a basic body can be influenced to restrict flexing effects during loading of the flap and of the basic body.

High lift system for an aircraft and method for influencing the high lift characteristics of an aircraft

A high lift component includes at least one intermediate seal on at least one lateral surface, wherein the intermediate seal includes at least one hollow body made of an elastic material, which hollow body includes a fluid inlet that is connectable to a fluid source. A gap between two high lift components, which gap is subjected to dynamic changes in geometry, can be flexibly sealed in this manner.

High lift component for an aircraft, high lift system, method for adjusting the high lift characteristics of an aircraft and aircraft

A leading edge slat arranged on the aerofoil of an aircraft. The leading edge slat is provided on the front of the main wing. The leading edge slat has a partially extended setting, with its trailing edge flat against the wing, and a further extended setting, with its trailing edge spaced apart from the nose of the wing to open a gap feeding high-energy air from the lower surface of the slat to the upper surface of the wing. The leading edge slat includes a body and a trailing edge facing the main wing, which can be bent around the spanwise direction of the slat relative to the body, and on which the trailing edge of the slat is provided, and which by means of a device generating a contact force is loaded for making contact between the trailing edge of the slat and the profile nose of the wing.

Fore flap disposed on the wing of an aircraft

An aircraft wing has a main wing element with a spar and a leading edge rib supported by the spar, a high lift device movably mounted to the main wing element, and an actuation mechanism with a drive shaft and a gear train. The gear train has a drive cog carried by the drive shaft, an actuator cog coupled to the high lift device, and one or more intermediate cogs mounted to the rib and coupled in series with the drive cog and the actuator cog so as to transmit torque from the drive cog to the actuator cog which moves the high lift device between a retracted position and an extended position in which the high lift device increases the camber of the wing. Sizes of the cogs in the gear train are selected so that the drive shaft rotates at a higher rate than the high lift device.

Leading edge rib assembly

The invention relates to a wing with an extension in the wingspan direction, in the wing chord direction and in the wing thickness direction for use in an aircraft, with a retractable wing end piece. A mechanical lever system is here used, which can execute a pivoting motion of a wing end piece comprising both a rotational component and a translational component. The lever kinematics here comprises two lever arrangements, for which a respective two hinged devices are provided.

Wing with retractable wing end piece

A flow body includes a flow body base body with a first shell element, a leading flow body edge with a second shell element and a clamping body, and a receiving space partially delimited by the clamping body. The flow body base body includes on a front end a projection, having a shape corresponding to that of the receiving space for engaging into the receiving space. The clamping body is internally arranged on the leading flow body edge spaced apart from a rear end of the second shell element. The rear end of the second shell element is flushly positioned on the first shell element when the projection engages into the receiving space. A smooth and harmonious transition that does not influence a laminar flow around the flow body can be achieved between the two components.

Flow body with a base body and a leading edge

A load introducing element for a control surface of an aircraft or a spacecraft comprises at least one first component, one second component and one first flange. At least one surface area of the first component is adapted to conform to the inner contour of the control surface. The second component has at least one eye for receiving bearing means for mounting the control surface. A cross sectional profile of the first component has two or more essentially straight legs, which are connected together on their upper side by an upper edge which is adapted to an upper contour of the control surface. The load introducing element is formed by a fiber reinforced composite material having an integral type of construction in which all of the components are jointly infiltrated and cured. The invention also provides a method for producing such a load introducing element, a drive armature and an aircraft that includes such a load bearing element.

Load introducing element

A wing is provided, including a high-lift flap arranged on the wing such that it is movable by means of at least two adjustment mechanisms arranged side-by-side in the spanwise direction of the wing and adjustable by means of a drive device. Each adjustment mechanism includes a first adjustment lever, articulated on a main wing surface via a first pivotal articulation, with the formation of a first rotation axis; a second adjustment lever, articulated on the high-lift flap via a second pivotal articulation, with the formation of a second rotation axis; and a central articulation, linking together the first and the second adjustment levers, with the formation of a third rotation axis. An intermediate articulated part is arranged on at least one of the adjustment mechanisms for coupling the first adjustment lever and the main wing surface, or for coupling the second adjustment lever and the high-lift flap.

Aerofoil comprising a high lift flap

A wing of an aircraft provided with a main wing and an arrangement of leading edge lifting bodies, which as seen with reference to the incident flow direction are arranged on the leading edge, which are adjustably arranged on the main wing one behind another as seen in the spanwise direction of the main wing by means of respectively two positioning devices spaced apart from one another in the spanwise direction of the main wing. The wing has a connecting device, which is coupled to each of two adjacent leading edge lifting bodies, wherein the connecting device is configured such that in the event of a fracture of a positioning device of a positioning body external forces acting on the latter are transferred via the respective connecting device to the leading edge lifting bodies coupled up via the latter.

Wing of an aircraft

A lift-augmenting leading edge flap for a carrying wing of an aircraft, wherein the flap comprises an essentially rigid main body which makes a transition from the first side to the second side of the wing the flap being adjustable by a retention- and actuation mechanism coupled between the flap and wing box, between a first, retracted, position and a second, extended, position, wherein the first transition region of the flap is slidable to rest in each position essentially free of any gap, against the first skin of the wing box or against the wing end cover, in relation to the wing end cover.

Growing community of inventors

Bremen, Germany

Xavier Hue