Airbus Operations Sl

Francisco José Cruz Dominguez

Francisco Javier Honorato Ruiz

Elena Arévalo Rodríguez

Enrique Guinaldo Fernandez

Carlos Garcia Nieto

Fernando Pereira Mosqueira

Andrea Ivan Marasco

Manuel Ariza Martín

Iker Vélez De Mendizàbal Alonso

Paula Màs Màs

Enrique Guinaldo Fernàndez

Elena Arévalo Rodriguez

A structure of a control surface for aircrafts, such as elevators, rudders, landing flaps, ailerons, and other similar lifting surfaces. The control surface includes a front spar, a rear spar, a plurality of ribs, at least one hinge fitting, and at least one actuator fitting, the hinge and actuator fittings joined with the front spar. A first rib is joined with a hinge fitting to form a first oblique angle with the front spar; a second rib is joined with an actuator fitting to form a second oblique angle with the front spar. The rear spar, located between the front spar and trailing edge of the control surface, extends only between the second rib and an outboard end of the control surface. The ribs are located in correspondence with the main torsion and bending load paths created in the control surface during flight, landing or takeoff.

Aircraft control surface

A method for manufacturing a monolithic torsion box inner structure of an aircraft lifting surface including: a) providing a set of laminated preforms of a composite material for forming said torsion box inner structure, each laminated preform being configured for constituting a part of one component of the torsion box inner structure; b) arranging the laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure the said laminated preforms; c) demoulding the curing tooling in a vertical direction.

Highly integrated inner structure of a torsion box of an aircraft lifting surface

Aircraft fuselage frame in composite material with stabilising ribs which, in at least a first sector (), comprises a frame () with an omega-shaped cross-section () formed by a top element (), two webs ('), two feet (&#x2032;) which includes at least one internal rib () formed by a top element () joined to the top element () of the frame (), a web (), two flanges (&#x2032;) joined to the webs (&#x2032;) of the frame () and a foot () aligned with the feet (&#x2032;) of the frame (). The invention also relates to a manufacturing procedure for the first sector () of the frame with stabilised web () comprising steps for: a) providing a frame () and at least one internal rib () with the configurations indicated; b) joining at least said internal rib () to the frame ().

Aircraft fuselage frame of composite material with stabilising ribs

Load introduction zone in the rear end of an aircraft comprising receiving elements () of the loads of the horizontal and vertical tail stabilizers connected to structural elements () wherein: a) said structural elements are the cladding (), two contiguous load-bearing frames () with a &#x3a0; or omega cross-section and, at least, a third frame (); b) the receiving element of the horizontal tail stabilizer load is a first fitting () structured as a torque box, transversely arranged between said load-bearing frames () and connected to them, and the receiving elements of the vertical tail stabilizer loads are some second fittings () coupled to these frames (); c) said frames () and said first and second fittings () are entirely made of composite material.

Structure of the load introduction zone in the rear end of an aircraft

Growing community of inventors

Getafe, Spain

Francisco José Cruz Dominguez