公开(公告)号：US20190126572A1

公开(公告)日：2019-05-02

申请号：US16128935

申请日：2018-09-12

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Iker VELEZ DE MENDIZABAL ALONSO ,  David APELLANIZ DE LA FUENTE ,  Esteban MARTINO-GONZALEZ - ARANJUEZ

IPC: B29C70/54 ,  B29C70/30

Abstract: A modular mold for producing a panel including a panel of fiber reinforced material. The panel is configured to form hollow cells having an undulated trapezoidal cross-section. The mold includes at least three molding bars for forming each hollow cell. One of the molding bars has a trapezoidal cross shape. The other two molding bars have a triangular cross shape. The trapezoidal molding bar is located between the two triangular molding bars. The three molding bars when put together its cross-section forms the shape of the trapezoidal cross-section of the hollow cell.

公开(公告)号：US20170334545A1

公开(公告)日：2017-11-23

申请号：US15523074

申请日：2015-10-30

Applicant: Airbus Operations, S.L.

Inventor： Enrique GUINALDO FERNANDEZ ,  Carlos GARCIA NIETO ,  Iker VELEZ DE MENDIZABAL ALONSO ,  Javier Francisco HONORATO RUIZ ,  Jose Francisco CRUZ DOMINGUEZ ,  Luis RAMOS GARCIA

IPC: B64C5/02 ,  B64C1/26

CPC classification number: B64C5/02 ,  B64C1/26

Abstract: An aircraft horizontal tail plane (HTP) of the continuous type, wherein the inner-most ribs of the right-hand side and left-hand side torsion boxes are arranged to have one end joined right at the joint zone where both rear spars meet at axis of symmetry of the HTP. In this way, the loads at this central region of the HTP are concentrated at the joint zone where the inner-most ribs and the rear spars converge. The HTP can be manufactured with a reduced number of components.

公开(公告)号：US20190264610A1

公开(公告)日：2019-08-29

申请号：US16281799

申请日：2019-02-21

Applicant: Airbus Operations S.L.

Inventor： Esteban MARTINO-GONZALEZ ,  Iker VELEZ DE MENDIZABAL ALONSO ,  Vasilis VOTSIOS ,  Guillermo NICOLAS GUTIERREZ ,  Diego SANCHEZ FRANCO ,  David MATESANZ HIDALGO ,  Jose Angel HERNANZ-MANRIQUE

IPC: F02C7/042

Abstract: An auxetic bi-stable structure that comprises an auxetic curved shell movable between a first and a second stable position, and a rigid element. At least part of the surface of the auxetic curved shell is joined to the rigid element such that the curved shell is movable with respect to the rigid element between the first and second stable positions.

公开(公告)号：US20190168480A1

公开(公告)日：2019-06-06

申请号：US16205973

申请日：2018-11-30

Applicant: Airbus Operations S.L.

Inventor： Esteban MARTINO-GONZALEZ ,  Iker VELEZ DE MENDIZABAL ALONSO ,  David APELLANIZ DE LA FUENTE

IPC: B32B3/12 ,  B64C3/26 ,  B64C1/12

Abstract: A deformable auxetic structure for absorbing energy of an impact that comprises a plurality of interconnected adjoining tridimensional auxetic cells where each tridimensional auxetic cell comprises at least one surface element and a plurality of legs extending from the surface, the plurality of legs and the surface element being configured such that the sectional cut of the structure in at least two planes perpendicular to the surface element follows an auxetic pattern.

公开(公告)号：US20170088249A1

公开(公告)日：2017-03-30

申请号：US15279586

申请日：2016-09-29

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Carlos GARCÍA NIETO ,  Iker VELEZ DE MENDIZABAL ALONSO ,  Enrique GUINALDO FERNANDEZ ,  Soledad CRESPO PEÑA

IPC: B64C3/18 ,  B29C70/48 ,  B64F5/00

CPC classification number: B64C3/187 ,  B29C70/48 ,  B29K2105/0872 ,  B29L2031/3085 ,  B64C3/20 ,  B64F5/45 ,  Y02T50/43

Abstract: The present disclosure refers to the configuration and manufacturing process of a rib for the construction of an aircraft torsion box. In the method, a flat stack of plies of composite material is layered up, which is then cut to form a flat pre-form having an outer contour having flanges, and an internal contour having two or more diagonal trusses with flanges at opposite sides. The flat pre-form is press-formed to fold the flanges of the outer and internal contour to form a rib pre-form, which is finally cured. The present disclosure also refers to a composite rib having a unitary body by forming a single pre-form of stacked plies. The present disclosure allows the manufacture of the rib in one-shot process, integrating all the ribs components such that the assembly time and cost of the rib are minimized.