Airbus Operations Sl

Airbus Espana, S.l.

Jorge Pablo Verde Preckler

José Alberto Cabello Moreno

Jose Alberto Cabello Moreno

Raul Carlos Llamas Sandin

Alfonso González Gozalbo

Raúl Carlos Llamas Sandin

Raúl Carlos Llamas Sandín

José Miguel Vizarro Toribio

Maria Caballero Asensio

José Luis Collado Briceño

Stephane Viala

Jose Luis Collado Briceno

Raul Carlos Llamas Sandín

Mats Gustavsson

María Caballero Asensio

Jose Miguel Vizarro Toribio

The invention relates to a structural configuration of the rear fuselage () of an aircraft with propeller engines () comprising propellers () formed in turn by blades (), the mentioned propeller engines () being located at the rear part of the aircraft and the empennage () of the aircraft in turn being located behind the plane of the propellers (), characterized in that the structural configuration of the rear fuselage () comprises an outer skin () and an inner skin (), both skins () being joined by means of radial elements () configuring cells (), such that the obtained structural configuration maximizes the torsional strength of the rear fuselage () of the aircraft in the event of damage of the mentioned rear fuselage () due to the detachment of one of the blades () of the propeller engines ().

Impact resistant aircraft fuselage

A covering of a fuselage for aircraft having propeller engines, including an opening which is surrounded by a structural frame formed by ribs and stringers of the aircraft around the area of maximum acoustic impact of the propeller engines. The opening further includes a non-structural panel joined to the structural frame by a non-rigid joint which considerably attenuates the vibrations through such joint, thus reducing the indirect acoustic noise and the indirect structural noise generated by the propeller engines inside the passenger cabin of the aircraft.

Acoustically attenuated fuselage for aircraft

A stabilizing and directional-control surface of an aircraft includes a vertical stabilizer and a rudder that deflects relative to the vertical stabilizer. The rudder includes an internal profile that is extendable and retractable by an actuating system. An aerodynamic control surface area of the rudder is increased when the internal profile of the rudder is extended as compared to the aerodynamic control surface area of the rudder when the internal profile of the rudder is retracted.

Stabilizing and directional-control surface of aircraft

The invention relates to a control surface () for an aerodynamic lifting surface () of aircraft comprising a main closing rib () located at one end of the control surface () to which a main torsion bar () is joined, the mentioned torsion bar () being joined at its other end to a lever system () on which at least one actuator () acts, such that it is possible to act on the rotation of the mentioned control surface () during the flight of the aircraft. The invention also relates to an actuation method for actuating such a control surface ().

Aircraft control device

The invention relates to a configuration of engines () for aircraft located in the rear part of the fuselage () of said aircraft, the engines () being attached in a fixed manner by pylons () to the structure of the aircraft, said structure comprising a torsion box () which traverses the fuselage () and is used to attach the pylons (), the fuselage () comprising an opening () allowing the passage of the suspension pylons () for the engines (), said configuration further comprising a pivoting area (), an actuator () and a fitting () through which the actuator () is attached to the suspension pylons () and to the torsion box () of the aircraft, such that the assembly formed by the actuator () and the fitting () allow balancing the pylon () and engine () assembly of the aircraft through the pivoting area (), thus achieving controllable and optimal thrust vectoring of the aircraft for each flight phase.

Optimized configuration of engines for aircraft

An aircraft tail assembly planform comprising curvilinear leading edges () and trailing edges (), with an aircraft tail assembly configuration in which the hinge line () is rectilinear and has a non-constant percentage with respect to the chord () in each section (), being the front () and rear () spars rectilinear with a non-constant percentage with respect to the chord () in each section (), or being these spars () curvilinear with a constant or non-constant percentage with respect to the chord () in each section (). Moreover, the invention describes an aircraft tail assembly planform comprising rectilinear leading edges () and trailing edges (), in which the hinge line () has a non-constant percentage with respect to the chord () in each section (), being the front () and rear () spars rectilinear, with a constant or non-constant percentage with respect to the chord () in each section (), or being these spars () curvilinear, with a constant or non-constant percentage.

Aircraft tail assembly

Growing community of inventors

Madrid, Spain

Jorge Pablo Verde Preckler