Eads Deutschland Gmbh

Airbus Deutschland Gmbh

Airbus Operations Gmbh

Airbus Defence and Space Gmbh

Juan Perez-Sanchez

Martin Voglsinger

Oliver Seack

Tamas Havar

Kay Dittrich

Tobias Ender

Hans Lonsinger

Claudia Bechheim

An effector for an aircraft has an effector body and a stealth sheath enclosing the effector body at least in part. The stealth shell is attached to the effector body and embodied so as to be separated from the aircraft and from the effector body during flight of the aircraft carrying the effector.

Effector with ejectable stealth shell

A lift flap bearing apparatus is improved with respect to aerodynamics, construction space and assembly, for guiding and adjusting a first lift flap and a second lift flap. The lift flap bearing apparatus comprises a first guiding device for guiding the first lift flap and a second guiding device for guiding the second lift flap. The first and the second guiding devices each have a first curved guide rail and a second curved guide rail.

Lift flap bearing apparatus, lift flap assembly, airfoil and aircraft

A wing, in particular a airfoil of an aircraft, with a variable profile shape, which wing comprises a first skin and a second skin and a supporting structure, arranged between the first and the second skin, which supporting structure in the direction of the wing depth extends between a first end and a second end, wherein the form of said supporting structure, for the purpose of varying the profile shape by means of a drive device comprising drive elements, is variable. The supporting structure comprises ribs, arranged one behind the other in the direction of the wing depth, which ribs at connection positions are interconnected so as to be articulated, wherein said ribs at first connection positions are connected to the first skin, and at second connection positions are connected to the second skin. For the purpose of setting the variable profile the mutual spacing of the second connection positions can be varied by means of the drive elements.

Wing, in particular airfoil of an aircraft, with a variable profile shape

System for opening and closing a structural part arranged on a support structure. The system includes at least one hinged joint device for flexibly connecting the structural part to the support structure. The at least one hinged joint device is arranged inside the support structure and has an axis of rotation about which the structural part can be pivoted relative to the support structure during opening and closing. A locking arrangement is structured and arranged to connect the structural part to the support structure in a form-locking manner when the structural part is in a closed position. In the closed position, the locking arrangement is arranged to relieve the at least one hinged joint device. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

Closure system for a support structure

A joint arrangement connects a longitudinal edge of a first component with an upper surface of a second component. At least two cooperating bands are secured with their first ends respectively on opposite sides of the first component, and are secured with their second ends respectively on clamping elements arranged on the second component, so that the bands intersect the major center plane of the first component in the joint area between the components. A pressure element is positioned on at least one clamping element for supporting the first component, and the bands extend laterally next to the pressure element and crosswise relative to one another.

Joint for connecting a longitudinal side to an upper side of components and flexible strip for use in such a joint

A wing has a changeable profile, and extends in a wing chord direction and perpendicularly thereto in a wingspan direction. The wing has a first cover skin and a second cover skin spaced apart from one another with spars therebetween. The wing includes a leading edge region and a trailing edge region opposite one another in the wing chord direction, and a wing tip region at the end of the wing in the wingspan direction. The wing further includes a flexible region that connects the wing tip region to the rest of the wing, and that is adapted to vary the profile of the wing in a direction that includes a component in the wing chord direction and a component in the wingspan direction.

Wing, especially a carrier wing of an airplane, having an adaptable profile

A pivoted flap mechanism for adjusting an aerodynamic pivotable flap associated with a wing, including: an actuating device including a gear device; a drive device including a drive arm that rotates about an axis, and which is structured and arranged to load the actuating device; and a flap support composed of a leading flap support portion and a trailing flap support portion. The aerodynamic pivotable flap is arranged on the flap support, and a steering arm of the gear device is swivellably coupled by a link to a part of the trailing flap support portion adjacent the leading flap support portion. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Pivoted flap mechanism for adjusting an aerodynamic pivoted flap associated with a wing

A structure with at least one flap connected to a wing, including: at least one drive device; at least one actuating device including a gear device coupled to the at least one drive device and the at least one flap; and a fairing housing swivellably mounted on the wing, at least partially surrounding the gear device, and coupled to the gear device, wherein actuation of the at least one drive device causes a combined translational and rotational movement of the at least one flap and a swivelling movement of at least a portion of the fairing housing. A method for pivoting a flap is also disclosed. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Wing with extendable aerodynamic pivoted flaps

System for opening and closing a structural part arranged on a support structure. The system includes at least one hinged joint device for flexibly connecting the structural part to the support structure. The at least one hinged joint device is arranged inside the support structure and has an axis of rotation about which the structural part can be pivoted relative to the support structure during opening and closing. A locking arrangement is structured and arranged to connect the structural part to the support structure in a form-locking manner when the structural part is in a closed position. In the closed position, the locking arrangement is arranged to relieve the at least one hinged joint device.

An aircraft wing including a wing box and a nose flap moveably connected to the wing box by first and second folding hinges. A first transverse link is pivotally connected to first portions of the first and second folding hinges. A second transverse link is pivotally connected to second portions of the first and second folding hinges. An actuator is connected diagonally between the first and second transverse links for moving the nose flap between a retracted position and an extended position. The instant abstract is neither intended to define the invention disclosed in the specification nor intended to limit the scope of the invention in any way.

Aircraft wing with extendible nose flap

A joint for the connection of components (T, T) that are movable relative to one another, on respective longitudinal sides (L, L), includes at least two cooperating bands, which are secured with their first ends (E) respectively on sides of the first component (T) lying opposite one another and with their second ends (E) respectively on sides of the second component (T) lying opposite one another, so that the paths of the bands extend opposite one another in relation to the center axes (A, A) of the components.

Joint for connecting components together on opposite longitudinal sides in addition to a flexible strip used for said joint

Lift flap mechanism for adjusting a lift flap assigned to an airplane wing by means of a driving system, the lift flap mechanism comprising a main connection mechanism and a secondary connection mechanism in the form of a guide lever disposed in an articulated manner on the lift flap and the flap track, the main connection mechanism having a steering lever arrangement with at least one steering lever which has a first steering lever joint and a second steering lever joint, the at least one steering lever by way of a pendulum coupled to the first steering lever joint being connected with the flap track, and the second steering lever joint being guided such that, by means of a defined angular position of the at least one steering lever, the positions of the main connection joint and of the secondary connection joint are unambiguously determined.

Lift-flap mechanism

Adjustment mechanism for adjustment area of variable-shape flow surface with two opposite skin surfaces includes plurality of whirl chambers swivelably arranged next to one another so that the whirl chambers are swivelable relative to one another, and the whirl chambers include lateral stiffening elements and longitudinal stiffening elements. Joints are structured and arranged to jointedly couple lateral stiffening elements and longitudinal stiffening elements of the whirl chambers, and a first drive tube section and a second drive tube section are arranged between adjacent longitudinal stiffening elements. A pump is coupled to first and second drive tube sections and control device is functionally connected to pump to swivel adjacent whirl chambers around joint axes via complementary volume changes in first and second drive tube sections. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Adjustment mechanism for a variable-shape wing

An actuation apparatus for a control flap which is disposed on the trailing edge of the wing of an aircraft and which can be displaced between a stowed position and an extended position, in which it is displaced rearwardly relative to the trailing edge of the wing and angled downwardly relative to the wing plane; and corresponding intermediate positions. The actuation apparatus has a pyramid mechanism arrangement connected, on the one hand, to the load-bearing structure of the wing and, on the other hand, to the control flap, with at least one virtual axis which lies, in particular, at a finite distance from the plane of the wing profile and relative to which the control flap can be displaced.

Growing community of inventors

Feldkirchen-Westerham, Germany

Juan Perez-Sanchez