Airbus Operations Sl

Airbus Espana, S.l.

Aiirbus Espana S. L.

Francisco Jose Cruz Dominguez

Francisco Javier Honorato Ruiz

Enrique Guinaldo Fernandez

Carlos Garcia Nieto

Iker Vélez De Mendizábal Alonso

Elena Arevalo Rodriguez

Paula Más Más

Jose David Cano Cediel

Enrique Guinaldo Fernadez

Maria Pilar Munoz Lopez

Iker Vélez De Mendizàbal Alonso

Paula Màs Màs

An aircraft lifting surface with a main supporting structure comprising upper and lower faces defining its aerodynamic profile, front and rear faces oriented towards, respectively, the leading and trailing edges, a first set of transverse ribs extended from the front face to the rear face and a second set of transverse ribs crossing the front face and/or the rear face. The integration of leading and trailing edge ribs in the main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. A manufacturing method of said main supporting structure is also disclosed.

Main supporting structure of an aircraft lifting surface

An aircraft lifting surface with a monolithic main supporting structure of a composite material including an upper skin having at least a part of the upper aerodynamic profile of the leading edge and/or of the trailing edge, a lower skin, a front spar, a rear spar, and leading edge ribs and/or a trailing edge ribs. The main supporting structure allows a weight and cost reduction of aircraft lifting surfaces.

Highly integrated structure including leading and trailing edge ribs for an aircraft lifting surface

A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demolding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.

Highly integrated leading edge of an aircraft lifting surface

A frame of a fuselage section of an aircraft that receives external loads, such as the rear section that receives the loads of the tail planes, comprising a first sector configured specifically to withstand these external loads and a second sector along the remaining perimeter of the fuselage, said first sector comprising the following structural elements a) a foot piece to be joined to the fuselage skin; b) a head piece; c) a web comprising one or more fitting-pieces for receiving said external loads and a plurality of X-shaped pieces joined by its ends to said foot piece and said head piece; and d) two connecting pieces of the ends of said foot piece and said head piece with the second sector of the frame.

Highly loaded frame of an aircraft fuselage with a lattice structured web

An aircraft lifting surface with a torsion box of a composite material including an upper skin, a lower skin, a front spar, a rear spar, one or more intermediate spars and transverse ribs arranged between the rear spar and an adjacent intermediate spar and/or between the front spar and the adjacent intermediate spar.

Optimized torsion box for an aircraft

A reinforcement structure for an opening in the primary structure of an aircraft, the structure comprising a skin, frame members which are transverse with respect to the flying direction of the aircraft, and stringers which are longitudinal with respect to the flying direction of the aircraft. The reinforcing structure includes a perimetral reinforcing element situated along the edge of the opening and reproducing the geometrical form thereof; at least one pair of transverse reinforcing elements arranged on both transverse sides of the opening; and at least one pair of longitudinal reinforcing elements arranged on both longitudinal sides of the opening.

Internal structure of aircraft made of composite material

The present invention relates to a curved rear pressure bulkhead () made of a composite material, comprising three layers: an outer layer () and an inner layer () symmetrical with one another, which are made of a fiber laminate, and the intermediate layer or core () made of a lightweight material. With such a sandwich-type shape, the resulting bulkhead () is able to withstand the bending loads coming from the strain and pressurization of the fuselage without having to increase its stiffness by means of using some type of stiffener. The bulkhead () comprises a ring () that is attached to the ends of the sandwich shape. This ring () is split into several parts () to facilitate the assembly of the bulkhead () made of composite material to the fuselage skin ().

Pressure bulkhead made of composite material for an aircraft

The invention relates to an integrated multispar torsion box structure of composite material for aircraft, comprising a lower skin (), an upper skin (), several spars (), each of which comprises in turn a chord () and a web (), several stringers () in the lower skin () and several stringers () in the upper skin (), characterized in that the mentioned integrated torsion box structure is achieved by means of joining unitary U-shaped structural elements (), unitary U-shaped structural elements () with a flap and unitary C-shaped structural elements () with a flap. The invention also relates to a method for manufacturing an integrated multispar torsion box structure of composite material for aircraft.

Growing community of inventors

Madrid, Spain

Francisco Jose Cruz Dominguez