Patents by Inventor Elena Arevalo Rodriguez

Elena Arevalo Rodriguez has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 11440634
    Abstract: A frame (1) for fuselage shells of an aircraft, the fuselage comprising a skin (3) and stringers (4), the frame (1) including: a plurality of sections (5), the sections (5) being separated by intermediate gaps corresponding to the position of the stringers (4) in the fuselage, each section (5) having a multi-cell configuration constituted by several modular elements (6) of composite material arranged in longitudinal direction, and a continuous inner cap (7) on top of the sections (5) and the intermediate gaps.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: September 13, 2022
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Elena Arevalo Rodriguez, Antonio Torres Esteban
  • Patent number: 10696377
    Abstract: A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: June 30, 2020
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Elena Arévalo Rodríguez, Francisco José Cruz Domínguez, Ana Reyes Moneo Peñacoba
  • Publication number: 20200156758
    Abstract: A frame assembly for a rear section of an aircraft, comprising at least one frame having a plane of symmetry, wherein the frame assembly also comprises at least one supporting element having two ends, wherein each one of the ends is attached to said at least one frame at different sides of the plane of symmetry. This arrangement permits a more effective transfer of loads coming from the vertical tail plane of the aircraft to the fuselage.
    Type: Application
    Filed: November 14, 2019
    Publication date: May 21, 2020
    Inventors: Nuria COLMENAREJO MATELLANO, Maria Almudena CANAS RIOS, Elena AREVALO RODRIGUEZ, Francisco Jose CRUZ-DOMINGUEZ, Jesus Javier VAZQUEZ CASTRO
  • Publication number: 20200108905
    Abstract: A frame (1) for fuselage shells of an aircraft, the fuselage comprising a skin (3) and stringers (4), the frame (1) including: a plurality of sections (5), the sections (5) being separated by intermediate gaps corresponding to the position of the stringers (4) in the fuselage, each section (5) having a multi-cell configuration constituted by several modular elements (6) of composite material arranged in longitudinal direction, and a continuous inner cap (7) on top of the sections (5) and the intermediate gaps.
    Type: Application
    Filed: July 24, 2019
    Publication date: April 9, 2020
    Inventors: Elena AREVALO RODRIGUEZ, Antonio TORRES ESTEBAN
  • Publication number: 20170341729
    Abstract: A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.
    Type: Application
    Filed: December 21, 2015
    Publication date: November 30, 2017
    Applicant: Airbus Operations S.L.
    Inventors: Elena ARÉVALO RODRÍGUEZ, Francisco José CRUZ DOMÍNGUEZ, Ana Reyes MONEO PEÑACOBA
  • Patent number: 9771140
    Abstract: The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.
    Type: Grant
    Filed: December 25, 2013
    Date of Patent: September 26, 2017
    Assignee: Airbus Operations S.L.
    Inventors: Elena Arevalo Rodriguez, Estelle Baligand
  • Patent number: 9637216
    Abstract: An aircraft structure made of composite material, comprising a skin reinforced longitudinally with stringers, and frames perpendicular to the stringers, each stringer comprising a head and two webs, and each frame having recesses in its web for the passage of the longitudinal stringers, such that an internal preform is provided in the gap existing between each stringer and the skin, filling the gap.
    Type: Grant
    Filed: December 30, 2014
    Date of Patent: May 2, 2017
    Assignee: Airbus Operations S.L.
    Inventor: Elena Arevalo Rodriguez
  • Publication number: 20160185437
    Abstract: A tail cone of an aircraft, more specifically a tail cone made of composite materials comprising an internal skin, an external skin surrounding the internal skin, longitudinal structural members located on the inner face of the internal skin in the longitudinal direction of the tail cone, and transversal structural members located between the external skin and the internal skin in the transverse direction of the tail cone.
    Type: Application
    Filed: December 22, 2015
    Publication date: June 30, 2016
    Inventor: Elena Arevalo Rodriguez
  • Patent number: 9216810
    Abstract: A frame of a fuselage section of an aircraft that receives external loads, such as the rear section that receives the loads of the tail planes, comprising a first sector configured specifically to withstand these external loads and a second sector along the remaining perimeter of the fuselage, said first sector comprising the following structural elements a) a foot piece to be joined to the fuselage skin; b) a head piece; c) a web comprising one or more fitting-pieces for receiving said external loads and a plurality of X-shaped pieces joined by its ends to said foot piece and said head piece; and d) two connecting pieces of the ends of said foot piece and said head piece with the second sector of the frame.
    Type: Grant
    Filed: November 29, 2012
    Date of Patent: December 22, 2015
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Francisco Jose Cruz Dominguez, Elena Arevalo Rodriguez
  • Publication number: 20150183504
    Abstract: An aircraft structure made of composite material, comprising a skin reinforced longitudinally with stringers, and frames perpendicular to the stringers, each stringer comprising a head and two webs, and each frame having recesses in its web for the passage of the longitudinal stringers, such that an internal preform is provided in the gap existing between each stringer and the skin, filling the gap.
    Type: Application
    Filed: December 30, 2014
    Publication date: July 2, 2015
    Inventor: Elena Arevalo Rodriguez
  • Patent number: 8870117
    Abstract: Composite aircraft frame (1) comprising two segments (10, 20), each of these segments (10, 20) being single unitary element made in composite material and comprising at least one web (2), a stiffening structure and a fitting (4), the two segments (10, 20) being joint by the fittings (4) using rivets, forming the aircraft frame (1). The invention also refers to a method for fabricating such an aircraft frame (1).
    Type: Grant
    Filed: December 28, 2011
    Date of Patent: October 28, 2014
    Assignee: Airbus Operations S.L.
    Inventors: María Pilar Muñoz López, Elena Arévalo Rodríguez, Javier Cabeza Huertas, Enrique Vera Villares, Melania Sánchez Pérez
  • Patent number: 8783618
    Abstract: Weathertight fitting (41) for the mounting of the tail vertical stabilizer of an aircraft in a rear area of its fuselage, the construction being based on a casing (5) made with a composite material as one unitary piece and some frames (7) that are comprised of: one first piece (43) comprised of two bodies (45, 45?), that include the mounting lugs (47, 47?) for the tail vertical stabilizer and some vertical walls (49, 49?) for joining the fitting (43) to the frames (7) of the fuselage, and a weathertight central profile (51); two pairs of additional pieces (55, 55?; 65, 65?) of angular shape, that include some horizontal walls (57, 57?; 67, 67?) for joining to the casing (5) and some vertical walls (59, 59?; 69, 69?) for joining to the aforementioned bodies (45, 45?). All the weathertight fitting's (41) pieces are made with a composite material.
    Type: Grant
    Filed: July 20, 2011
    Date of Patent: July 22, 2014
    Assignee: Airbus Operations S.L.
    Inventors: Enrique Vera Villares, Elena Arévalo Rödríguez, José Maria Pina López, Javier Cabeza Huertas, Diego Folch Cortés
  • Patent number: 8777159
    Abstract: A reinforcement structure for an opening in the primary structure of an aircraft, the structure comprising a skin, frame members which are transverse with respect to the flying direction of the aircraft, and stringers which are longitudinal with respect to the flying direction of the aircraft. The reinforcing structure includes a perimetral reinforcing element situated along the edge of the opening and reproducing the geometrical form thereof; at least one pair of transverse reinforcing elements arranged on both transverse sides of the opening; and at least one pair of longitudinal reinforcing elements arranged on both longitudinal sides of the opening.
    Type: Grant
    Filed: May 24, 2011
    Date of Patent: July 15, 2014
    Assignee: Airbus Operations S.L.
    Inventors: Francisco Jose Cruz Dominguez, Elena Arevalo Rodriguez
  • Publication number: 20140186572
    Abstract: The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas.
    Type: Application
    Filed: December 25, 2013
    Publication date: July 3, 2014
    Inventors: Elena Arevalo Rodriguez, Estelle Baligand
  • Patent number: 8597771
    Abstract: Aircraft fuselage frame (9) in composite material with stabilized web whose omega-shaped cross section (11) in at least a first segment (31) is formed by one head (23), two webs (25, 25?), two feet (27, 27?) with a stiffening element (29) between the two webs (25, 25?). The invention also refers to a manufacturing procedure for the first segment (31) comprising steps to: a) provide an external element (41) with an omega-shaped cross section formed by one head (43), two webs (45, 45?) and two feet (47, 47?), and an internal element (51) with omega-shaped section formed by one head (53), two webs (55, 55?) and two feet (57, 57?), with their respective webs (45, 55; 45?, 45?) and feet (47, 57; 47?, 57?) oriented in parallel; b) join the internal element (51) to the external element (41).
    Type: Grant
    Filed: December 29, 2010
    Date of Patent: December 3, 2013
    Assignee: Airbus Operations S.L.
    Inventor: Elena Arévalo Rodríguez
  • Patent number: 8592026
    Abstract: Aircraft fuselage frame in composite material with stabilising ribs which, in at least a first sector (31), comprises a frame (9) with an omega-shaped cross-section (11) formed by a top element (23), two webs (25, 25?), two feet (27, 27?) which includes at least one internal rib (41) formed by a top element (43) joined to the top element (23) of the frame (9), a web (45), two flanges (49, 49?) joined to the webs (25, 25?) of the frame (9) and a foot (47) aligned with the feet (27, 27?) of the frame (9). The invention also relates to a manufacturing procedure for the first sector (31) of the frame with stabilised web (10) comprising steps for: a) providing a frame (9) and at least one internal rib (41) with the configurations indicated; b) joining at least said internal rib (41) to the frame (9).
    Type: Grant
    Filed: September 16, 2010
    Date of Patent: November 26, 2013
    Assignee: Airbus Operations S.L.
    Inventors: Elena Arévalo Rodríguez, Francisco José Cruz Dominguez
  • Patent number: 8418963
    Abstract: The present invention relates to an aircraft load frame (1) made of a composite material, characterized in that it comprises two side elements (2, 3) and a base element (7), the side elements (2, 3) being joined at the inner part of the frame (1) by means of the base element (7) and each of the side elements (2, 3) comprising a leg (4) joining the frame (1) to the aircraft fuselage skin, a web (5) and a lower flange (6) joining the web (5) and the base element (7).
    Type: Grant
    Filed: March 29, 2007
    Date of Patent: April 16, 2013
    Assignee: Airbus Operations S.L.
    Inventors: Elena Arévalo Rodríguez, Cesar Bautista De La Llave, Cristina Ortega Juaristi
  • Patent number: 8408495
    Abstract: A fitting is provided to fix a vertical tail stabilizer of an aircraft to a composite skin and a composite frame of the aircraft in an area of a rear fuselage thereof. The fitting includes a first composite piece having lugs to attach to the vertical tail stabilizer and having vertical walls to fix the fitting to the composite frame of the rear fuselage. The fitting further includes at least one pair of additional composite pieces, each having a horizontal wall to fix the fitting to the composite skin of the rear fuselage. A second pair of additional composite pieces may be provided to further secure the fitting to the skin of the aircraft.
    Type: Grant
    Filed: February 26, 2010
    Date of Patent: April 2, 2013
    Assignee: Airbus Operations, S.L.
    Inventors: Diego Folch Cortés, Enrique Vera Villares, Javier Cabeza Huertas, José María Pina López, Elena Arévalo Rodríguez
  • Publication number: 20120305707
    Abstract: Composite aircraft frame (1) comprising two segments (10, 20), each of these segments (10, 20) being single unitary element made in composite material and comprising at least one web (2), a stiffening structure and a fitting (4), the two segments (10, 20) being joint by the fittings (4) using rivets, forming the aircraft frame (1). The invention also refers to a method for fabricating such an aircraft frame (1).
    Type: Application
    Filed: December 28, 2011
    Publication date: December 6, 2012
    Inventors: María Pilar MUÑOZ LÓPEZ, Elena ARÉVALO RODRÍGUEZ, Javier CABEZA HUERTAS, Enrique VERA VILLARES, Melania SÁNCHEZ PÉREZ
  • Patent number: 8267352
    Abstract: Load introduction zone in the rear end of an aircraft comprising receiving elements (3, 4) of the loads of the horizontal and vertical tail stabilizers connected to structural elements (2, 8, 9) wherein: a) said structural elements are the cladding (8), two contiguous load-bearing frames (2) with a ? or omega cross-section and, at least, a third frame (9); b) the receiving element of the horizontal tail stabilizer load is a first fitting (3) structured as a torque box, transversely arranged between said load-bearing frames (2) and connected to them, and the receiving elements of the vertical tail stabilizer loads are some second fittings (4) coupled to these frames (2, 9); c) said frames (2, 9) and said first and second fittings (3, 4) are entirely made of composite material.
    Type: Grant
    Filed: February 19, 2009
    Date of Patent: September 18, 2012
    Assignee: Airbus Operations S.L.
    Inventors: Manuel Ariza Martín, Elena Arévalo Rodríguez, Francisco José Cruz Dominguez