Airbus Operations Sl

Airbus Espana, S.l.

Pablo Timoteo Sanz Martínez

Diego Folch Cortés

Eduardo Vinué Santolalla

Ana Reyes Moneo Peñacoba

Raúl Carlos Llamas Sandín

César Bautista De La Llave

Esteban Martino Gonzáles

An aircraft fuselage part () located in a section of an aircraft () having a propulsion system () attached by upstream pylons (), the fuselage part includes a skin (); a plurality of frames () arranged perpendicularly to a longitudinal axis (); a single or internally divided upper longitudinal box () and a single or internally divided lower longitudinal box () which are configured to form with the skin () a multi-cell structure, belonging in each cell the external side to the skin () and the internal sides to the longitudinal boxes (); a plurality of lateral beams () that are interconnected with the frames () to form together with the skin () a structural unity. The fuselage components () are dimensioned so that the aircraft can withstand the effect of pre-defined failure events keeping a sufficient number of closed cells.

Impact resistant and damage tolerant aircraft fuselage

Aircraft control surface (), in particular for an aircraft lifting surface (), that comprises a primary control surface () that comprises a hinge axis (), and a secondary control surface () that comprises a hinge axis (), with the secondary control surface () rotating by means of its hinge axis () relative to the primary control surface (), said secondary control surface () only partially occupying the span of the primary control surface (), the length of the secondary control surface () along its hinge axis () being significantly less than the length of the primary control surface () along its hinge axis (), and moreover the width or chord of said secondary control surface () along the direction of its hinge axis () narrows significantly towards the tip of the lifting surface () according to a law of narrowing designed expressly for adapting the distribution of torsional stiffness along the span of the lifting surface () to the distribution of aerodynamic load thereon, whereas the distribution of effective curvature due to the deflection of said control surface () is such that it increases the stalling angle of the lifting surface ().

Control surface of aircraft

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Madrid, Spain

Pablo Timoteo Sanz Martínez