Airbus Operations Sl

Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Esteban Martino Gonzalez

Diego Folch Cortes

Pablo Goya Abaurrea

Eduardo Vinue Santolalla

Enrique Guinaldo Fernandez

Julien Guillemaut

Vasilis Votsios

Jérôme Colmagro

Jonathan Blanc

Fernando Pereira Mosqueira

Sylvain Roumegas

Sandra Linares Mendoza

Wolfgang Brochard

Lionel Diochon

Eric Bouchet

Pedro Nogueroles Viñes

Juan Tomas Prieto Padilla

Andrea Ivan Marasco

Michel Fouinnetau

Javier Toral Vazquez

Tamara Blanco Varela

Diego Folch Cortés

Angel Pascual Fuertes

Eduardo Vinué Santolalla

Pablo Timoteo Sanz Martinez

Javier Toral Vázquez

Daniel Redondo Garcia

Jose Antonio Mariblanca Lopez

Andrea Iván Marasco

Raúl Fernandez Ballesteros

Aitor Baldomir Garcia

Jacobo Diaz Garcia

Santiago Hernandez Ibanez

Javier Ruperez

David Alvaro Granero

An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.

Aircraft with a protective shield against an engine blade release

A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.

Impact resistant sandwich structure

An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.

Aircraft fuselage frame

An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone.

Aircraft rear structure

The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.

Propeller blade for an aircraft engine

A deformable structure, such as a panel or a shock absorber, for absorbing energy from a mechanical and/or acoustic impact. The structure comprises an inner core and one or more external layers covering the inner core. The inner core comprises a set of first segments having a positive Poison's ratio and second segments having a negative Poisson's ratio. The first and second segments are arranged alternately and joined to one another so that the deformation received by one first segment is transmitted to an adjacent second segment and vice versa.

Deformable structure for absorption of energy from mechanical and/or acoustic impacts

An aircraft rear structure that comprises a rear pressure bulkhead, and a lifting surface located at both sides of the fuselage of the aircraft. The lifting surface comprises spars extending in the longitudinal direction of the lifting surface. The pressure bulkhead is aligned with one of the spars of the lifting surface.

In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.

Method for assembling an aircraft aft portion

A fuselage section of an aircraft includes a skin, a plurality of frames positioned transversely to a longitudinal axis of a fuselage of the aircraft, and a plurality of longitudinal stringers at least one of which is configured with a closed transversal section including a stringer hat, two stringer webs, and two stringer feet joined to the skin. At least one of the frames is configured in at least one sector with a frame foot joined to the skin, a frame web having holes at crossing zones with the stringers, a frame cap, and a frame cap extension which does not interfere with the stringers. The frames are joined to, at least, the stringer hats at crossing zones of the frames and the stringer hats.

Aircraft fuselage with high strength frames

Aircraft fuselage section () subjected to impacts of external bodies, the aircraft fuselage having a curved shape with at least a vertical symmetry plane (A-A) and a central longitudinal axis and comprising a skin () and a plurality of frames () arranged perpendicularly to said longitudinal axis (), the aircraft fuselage section also comprising at least an inner reticular structure () mounted on a supporting structure () comprising longitudinal beams () attached to the skin () and interconnected with said frames (), said inner reticular structure () being arranged for creating at least one closed cell () with the skin () for improving its resistance and its damage tolerance to said impacts. Said inner reticular structure () can be formed by panels (), rods (65, 65'), cables (67, 67&#x2032;) or belts (69, 69&#x2032;).

Impact resistant and damage tolerant aircraft fuselage

A computer-aided method for carrying out the structural design of a part subjected to damages having significant effects on its structural integrity, such as an aircraft fuselage section subjected to a propeller blade release event, is provided. The method includes: obtaining finite element models that include all the relevant information for an optimization analysis for the un-damaged part and for at least one possible damaged part; defining at least one design variable of the part and at least one design constraint and one load case for the un-damaged part and for the damaged part; providing at least one simulation module for analyzing one or more failure modes of the part; iteratively modifying the design variables of the part for the purpose of optimizing a target function by analyzing simultaneously the un-damaged part and the at least one damaged part using the at least one simulation module.

Multiple damage method for structural design optimization

Commercial aircraft () having a black box () comprising a flight data recorder () connected to suitable acquisition units () for recording information required for crash investigation purposes inside a container (), wherein the aircraft () comprises a crash detection device (); the black box () is installed in a suitable location for being ejected outside the aircraft in a crash event through a duct () having its exit in a fuselage area where the ejected black box () would not impact on the aircraft; the aircraft () also comprises ejection means (), controlled by a black box ejection control unit () connected to said crash detection device (), for ejecting the black box () through said duct (), when an impending crash is detected by said crash detection device ().

Aircraft black box

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Madrid, Spain

Esteban Martino Gonzalez