Airbus Operations Gmbh

Airbus Operations Sl

Alberto Balsa-Gonzalez

Robert Kobierecki

Jose Luis Lozano Garcia

Juan Antonio Sánchez Ruiz

Miguel Ángel Mendez Rodriguez

Javier Carlos Gomez Del Valle

Miguel Ángel Mendez Rodríguez

David Martin Palomares

A device and a process for manufacturing a composite part, the device comprising four molding mandrels that can be arranged in a mold arrangement in which they form a mold for the composite part, as well as a locking mandrel configured to lock the molding mandrels in the mold arrangement and to be extracted from between the molding mandrels to release the molding mandrels from their mold arrangement. The locking mandrel extends from one longitudinal end of the molding mandrels to another opposite longitudinal end of the molding mandrels.

Device comprising multiple longitudinal mandrels forming a mold for manufacturing a composite part

A manufacturing method of a control surface of an aircraft, the control surface including an upper skin, a lower skin, ribs joining the upper skin and the lower skin and located along a chordwise direction of the control surface. The manufacturing method includes the steps of providing a single composite preform comprising the upper skin, the lower skin and the ribs, and curing the single composite preform such that an integrated box comprising the upper skin, the lower skin and the ribs is formed.

Manufacturing method of a control surface of an aircraft and aircraft control surface

A multispar lifting surface including a multispar torsion box having corner reinforcements, a movable control surface, and an axial rod fitting. The movable control surface includes a movable element, a hinged connection joined to the movable element, and an axial rod joining the hinged connection to the rear spar of the multispar torsion box. The axial rod fitting is configured to join the axial rod and the multispar torsion box; and includes a longitudinal profile resting against the rear spar, and a lug joined to the longitudinal profile at one end and to the axial rod at another end; the lug defining a plane including the longitudinal axis of the axial rod. This multispar lifting surface is able to support sideward forces without any additional structure.

Multispar lifting surface

A trailing edge for a composite lifting surface is disclosed having a spar, an upper panel and a lower panel each having a free edge, a seal, and an elongated profile located on the panels following a spanwise direction of the trailing edge. An elongated profile including a web extending along the spanwise direction of the trailing edge, and having first and second flange portions, and a transition zone in between the first and second flange portions extending at different heights with respect to each other. The first flange portion is configured to hold at least a part of the seal underneath, and the second flange portion is configured to contact the panel so that the first flange portion secures the seal to the panel, and the second flange portion secures the elongated profile to the panel.

Trailing edge for a composite lifting surface

A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.

Flight control surface for an aircraft and method for manufacturing said flight control surface

A leading edge for an airfoil of an aircraft includes a leading plate with a convex side and a concave side, and at least one container filled with a non-Newtonian fluid. The leading edge is configured to be secured to the torsion box of the airfoil. The at least one container is arranged between the concave side of the leading plate and the torsion box of the airfoil. An airfoil is also provided including such a leading edge. A method is provided for assembling such a leading edge.

Leading edge for an airfoil

A trailing edge for a composite multispar integrated lifting surface includes a first C-shape composite form that includes a web and two flanges. The web forming a portion of the rear spar of a torsion box. The two flanges extending along a skin chordwise direction. A second C-shape composite form includes a web and two flanges. The web forms an auxiliary spar. The flanges extend along the skin chordwise direction. The first C-shape composite form and the second C-shape composite form forming a first auxiliary cell and a second cell. The first auxiliary cell is delimited by the first C-shape composite form and the second C-shape composite form. The second cell is an open cell delimited by the second C-shape composite form.

Trailing edge for a composite multispar integrated lifting surface and method for manufacturing said trailing edge

A leading edge () of a control surface () for an aircraft includes a balance weight () attached to the forward-most region of the leading edge (). The control surface () rotates with respect to the stabilizer () around a hinge line (). The balance weight () is ahead of and adjacent to the most frontal portion () of the leading edge () of the control surface () are is inside the trailing edge of the stabilizer (). This arrangement allows to have an anti-flutter balance weight without any impact in aerodynamic drag.

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Getafe, Spain

Alberto Balsa-Gonzalez