Airbus Operations Sl

Airbus Operations (s.a.s.)

Other

Airbus Operations Gmbh

Airbus (sas)

Esteban Martino González

Jérôme Colmagro

Iker Vélez De Mendizábal Alonso

Pablo Goya Abaurrea

Adeline Soulie

Wolfgang Brochard

Julien Cayssials

Julien Guillemaut

Eric Bouchet

Jonathan Blanc

Alberto Arana Hidalgo

Edouard Menard

Fernando Iniesta Lozano

Didier Poirier

Diego Folch Cortes

Carlos García Nieto

Enrique Guinaldo Fernández

Jesús Javier Vázquez Castro

Pablo Cebolla Garrofe

Soledad Crespo Peña

Juan Tomas Prieto Padilla

Tamara Blanco Varela

Alfonso Parra Rubio

Thomas Stevens

Diego Folch Cortés

Diego Barron Vega

Eduardo Vinue Santolalla

David Apellaniz De La Fuente

Javier Toral Vazquez

Pierre-Alain Pinault

Michel Fouinnetau

Sylvain Roumegas

Bruno Medda

Eduardo Vinué Santolalla

Elena Moya Sanz

Javier Toral Vázquez

José Luis Martínez Muñoz

Jorge Antonio Bes Torres

Álvaro Jara Rodelgo

Pablo Vázquez Sánchez

Vasillis Votsios

Pablo Goya Albaurrea

José María Pina LÓPEZ

Sandra Liñares Mendoza

Diego Folch CORTÉS

Vasilis Votsios

Javier Toral Vàzquez

ÁNgel Pascual Fuertes

Julien Gillemaut

An airfoil of an aerodynamic surface including: a control surface having an upper surface and a lower surface, and an actuator configured to elevate or lower the control surface, wherein at least a portion of one of the upper surface and the lower surface of the control surface is auxetic with a negative Poisson ratio, and the other of the upper surface and the lower surface of the control surface includes a material with a higher Poisson ratio.

Airfoil of an aerodynamic surface

A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.

Three dimensional auxetic structure, manufacturing method and tooling

An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

Aircraft propulsion system including a heat exchanger system

An impact resistant fuselage of an aircraft, the fuselage extending along a central longitudinal direction, wherein transversal sections of the fuselage are comprised in a vertical plane perpendicular to the central longitudinal direction. The impact resistant fuselage comprises at least a ballistic material membrane extended along the longitudinal direction for absorbing high energy impacts. The membrane according to a transversal section, comprising at least one section between two tensional elements, wherein the material membrane is located inside the fuselage of the aircraft, the at least one section of the membrane is mechanically linked to the inside of the fuselage by the tensional elements, and the two tensional elements stress the membrane.

Impact resistant fuselage

An energy absorbing structure for attenuating energy received from an energy source. The structure comprises a deformable structure formed by an ensemble of one or more first layers of a material having a positive Poisson's ratio, one or more second layers of a material having a negative Poisson's ratio and one or more third layers of an elastomeric material placed between a first layer and a second layer. The ensemble is arranged with the one or more third layers joined to the first and second layers for absorbing at least part of the energy through shear forces or a combination of traction and compression forces applied to the ensemble by the first and second layers as a consequence of their differential deformation after receiving the energy.

Energy absorbing structure for attenuating the energy transmitted from an energy source

An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material layer is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.

Impact resistant dorsal fin

A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.

Integrated detachable ballistic shield

A self-destruction device adapted to be installed in a propeller blade, the self-destruction device including a detector adapted to detect a release of the propeller blade, a warning mechanism adapted to send a release alarm in the event of the detector detecting release of the propeller blade, and a destruction mechanism adapted to destroy the propeller blade in the event of receiving a release alarm from the warning mechanism. An engine and an aircraft are also provided.

Device for a propeller blade

Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.

Aircraft with fuselage-mounted engines and an internal shield

A method of designing an aircraft component formed by a number of elements that includes a phase to estimate the effect of a variation of a design variable on the component weight which method includes the following steps: a) providing the main primary structure basic data of the aircraft component and the Reserve Factors associated to its design criteria; b) obtaining a breakdown of the component weight by such design criteria using a fictitious weight calculated taking into account the relative importance of their critical design criteria; c) obtaining the weight effect of a design variable variation, recalculating firstly the new Reserve Factors using suitable functions for the variation of the Reserve Factors vs. the variation of the design variable and, secondly, recalculating the component weight using suitable functions for the variation of the element dimensions vs. the variation of the Reserve Factors.

Methods for estimating the effect of variations of design variables on the weight of an aircraft component

Growing community of inventors

Getafe, Spain

Esteban Martino González