Airbus Operations Sl

Airbus Operations Gmbh

Airbus Espana, S.l.

Raul Carlos Llamas Sandin

Daniel Reckzeh

Diego García Martín

Alfonso González Gozalbo

Nicolas Bailey Noval

Jorge Pablo Verde Preckler

Miguel Luque Buzo

José Alberto Cabello Moreno

Pablo Timoteo Sanz Martinez

José Luis Collado Briceño

Stephane Viala

Jose Miguel Vizarro Toribio

An aircraft () including an aerodynamic surface (), an aerodynamics improvement device with a first electrode () embedded beneath and electrically isolated from the aerodynamic surface (), a second electrode () electrically isolated from the first electrode (), a voltage generator () adapted to apply a voltage between the first and the second electrode, further comprising a layer of electrically insulating material () between the second electrode () and the aerodynamic surface (). Methods for detecting ice on and de-icing an aerodynamic surface (), and for delaying a boundary layer transition and separation from the aerodynamic surface.

Aerodynamics improvement device for an aircraft and aircraft equipped with such device

An aircraft comprising a fuselage extending along a longitudinal axis between a fore section and an aft section, wings mounted to the fuselage, a tail unit mounted to the aft section of the fuselage, and a first propulsion unit and a second propulsion unit both mounted to the aft section of the fuselage in such a way that a first axis of rotation of the first propulsion unit and a second axis of rotation of the second propulsion unit both extend in a vertical center plane spanned by the longitudinal axis and a yaw axis. The provided centerline mounted double-engine aircraft allows for a simple manufacture, maintenance and retrofit of the engines, in that the first propulsion unit and/or the second propulsion unit are arranged outside the fuselage.

Aircraft

A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.

Aircraft hybrid engine having gear ring encased fans

A multi-fan engine including a gas turbine engine, a casing and fans encased by geared rings, which connect with the geared rings of an adjacent fan(s) such that the rotation of one fan rotates the other fans. Intermediate gears may prove the connection between adjacent geared rings, wherein the intermediate gears are retracted by linear actuators to disengage the intermediate gears from the geared rings and thereby disengage the fans from each other. The multi-fan engine may be mounted flush to the fuselage of an aircraft invention to capture into the fans boundary layer airflow moving over the skin of the fuselage.

Multi-fan engine with an enhanced power transmission

A rear fuselage section of an aircraft comprises at least one closed frame constructed as a unitary body, and a horizontal tail plane comprising a box-type central element and two lateral torsion boxes, said horizontal tail plane trimmable with respect to a pivot axis. The horizontal tail plane is mounted at the closed frame and the pivot axis is contained in a horizontal plane below the lowest end of said closed frame.

Rear fuselage section of an aircraft

An aircraft tail surface, such as a horizontal tail plane or a vertical tail plane, including a leading edge having, in at least a section along the tail span, an undulated shape formed by a continuous series of smooth protrusions and recesses so that, in icing conditions, the ice accretion is produced only on the peaks of the protrusions and on the bottoms of the recesses, thereby creating a channeled airflow and an arrangement of air vortices which impart energy to the airflow in the aerofoil boundary layer which delay the airflow separation that causes the stall, thus reducing the detrimental effects of ice accretion in its aerodynamic performance.

Aircraft tail surface with a leading edge section of undulated shape

An aircraft () horizontal stabilizer () which can vary its sweep angle () by rotating around an essentially vertical axis () with respect to the direction of flight of the aircraft () when the aircraft () is in flight at high speeds, close to the speed of sound, this axis () being contained in the plane of symmetry of the aforementioned aircraft (), the aforementioned horizontal stabilizer () being is a single and structurally continuous component such that it does not transmit a bending moment to the fuselage () structure of the aircraft (), which permits it to be of reduced weight, such that the horizontal stabilizer () rotates in a single way and a single direction around the axis () to achieve the sweep angle () required for high-speed flight.

Pivoting stabilising surface for aircraft

An aircraft having a lambda-box wing configuration includes, a fuselage, a propulsion system, a first pair of swept-back airfoils, connected to the top forward portion of the fuselage, a second pair of swept-forward airfoils, connected to the lower rear portion of the fuselage at a point of the said fuselage aft of the connection of the swept-back airfoils, and a third pair of substantially vertical airfoils, the tips of the swept-forward airfoils being connected to the lower side of the swept-back airfoils at an intermediate point of the span of the said swept-back airfoils, by the substantially vertical airfoils, the swept-back airfoils having a higher aspect ratio than that of the swept-forward airfoils, which makes the swept-back airfoils have a reduced induced drag without penalizing their weight.

Aircraft having a lambda-box wing configuration

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 ().

Growing community of inventors

Getafe, Spain

Raul Carlos Llamas Sandin