Airbus Operations Sl

Elena Arévalo Rodríguez

Enrique Vera Villares

Francisco José Cruz Dominguez

Javier Cabeza Huertas

Diego Folch Cortés

Francisco José Cruz Domínguez

Ana Reyes Moneo Peñacoba

José María Pina López

Cesar Bautista De La Llave

María Pilar Muñoz López

Melania Sánchez Pérez

Cristina Ortega Juaristi

Manuel Ariza Martín

Pedro Luis Muñoz Royo

Francisco José Cruz DOMÍNGUEZ

José María Pina LÓPEZ

Javier Cabeza Huerta

A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

Fuselage rear end of an aircraft

Composite aircraft frame () comprising two segments (), each of these segments () being single unitary element made in composite material and comprising at least one web (), a stiffening structure and a fitting (), the two segments () being joint by the fittings () using rivets, forming the aircraft frame (). The invention also refers to a method for fabricating such an aircraft frame ().

Composite aircraft frame

Aircraft fuselage frame () in composite material with stabilized web whose omega-shaped cross section () in at least a first segment () is formed by one head (), two webs ('), two feet (&#x2032;) with a stiffening element () between the two webs (&#x2032;). The invention also refers to a manufacturing procedure for the first segment () comprising steps to: a) provide an external element () with an omega-shaped cross section formed by one head (), two webs (&#x2032;) and two feet (&#x2032;), and an internal element () with omega-shaped section formed by one head (), two webs (&#x2032;) and two feet (&#x2032;), with their respective webs (&#x2032;) and feet (&#x2032;) oriented in parallel; b) join the internal element () to the external element ().

Aircraft fuselage frame in composite material with stabilized web

Aircraft fuselage frame in composite material with stabilising ribs which, in at least a first sector (), comprises a frame () with an omega-shaped cross-section () formed by a top element (), two webs ('), two feet (&#x2032;) which includes at least one internal rib () formed by a top element () joined to the top element () of the frame (), a web (), two flanges (&#x2032;) joined to the webs (&#x2032;) of the frame () and a foot () aligned with the feet (&#x2032;) of the frame (). The invention also relates to a manufacturing procedure for the first sector () of the frame with stabilised web () comprising steps for: a) providing a frame () and at least one internal rib () with the configurations indicated; b) joining at least said internal rib () to the frame ().

Aircraft fuselage frame of composite material with stabilising ribs

The present invention relates to an aircraft load frame () made of a composite material, characterized in that it comprises two side elements () and a base element (), the side elements () being joined at the inner part of the frame () by means of the base element () and each of the side elements () comprising a leg () joining the frame () to the aircraft fuselage skin, a web () and a lower flange () joining the web () and the base element ().

Aircraft load frame made of a composite material

A fitting is provided to fix a vertical tail stabilizer of an aircraft to a composite skin and a composite frame of the aircraft in an area of a rear fuselage thereof. The fitting includes a first composite piece having lugs to attach to the vertical tail stabilizer and having vertical walls to fix the fitting to the composite frame of the rear fuselage. The fitting further includes at least one pair of additional composite pieces, each having a horizontal wall to fix the fitting to the composite skin of the rear fuselage. A second pair of additional composite pieces may be provided to further secure the fitting to the skin of the aircraft.

Fittings for attaching the vertical tail stabilizer of an aircraft

Load introduction zone in the rear end of an aircraft comprising receiving elements () of the loads of the horizontal and vertical tail stabilizers connected to structural elements () wherein: a) said structural elements are the cladding (), two contiguous load-bearing frames () with a &#x3a0; or omega cross-section and, at least, a third frame (); b) the receiving element of the horizontal tail stabilizer load is a first fitting () structured as a torque box, transversely arranged between said load-bearing frames () and connected to them, and the receiving elements of the vertical tail stabilizer loads are some second fittings () coupled to these frames (); c) said frames () and said first and second fittings () are entirely made of composite material.

Structure of the load introduction zone in the rear end of an aircraft

Integrated aircraft structure in composite material that comprises a skin and stringers (), with the skin comprising a string part () and a basic skin (), which structure further comprises U-shaped elements () each of which comprises in its turn two L-shaped sections (and) together with the skin part (), in such a way that these U-shaped elements () fulfill two structural functions in said structure at the same time, acting as frame feet and as skin, providing an integrated fuselage structure without rivets or joints. The invention also relates to a manufacturing process of an integrated aircraft structure in composite material.

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Madrid, Spain

Elena Arévalo Rodríguez