Airbus Operations Sl

Airbus Operations (s.a.s.)

Eduardo Vinue Santolalla

Esteban Martino Gonzalez

Enrique Guinaldo Fernandez

Diego Folch Cortes

Julien Guillemaut

Esteban Martino González

Pablo Goya Abaurrea

Tamara Blanco Varela

Andrea Ivan Marasco

Aitor Baldomir Garcia

Jacobo Diaz Garcia

Santiago Hernandez Ibanez

Pablo Goya Albaurrea

Diego Folch CORTÉS

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

Growing community of inventors

Madrid, Spain

Eduardo Vinue Santolalla