Patents by Inventor Elena Arévalo Rodríguez
Elena Arévalo Rodríguez 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).
-
Publication number: 20120091275Abstract: Weathertight fitting (41) for the mounting of the tail vertical stabiliser 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 stabiliser 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: ApplicationFiled: July 20, 2011Publication date: April 19, 2012Applicant: Airbus Operations S.L.Inventors: Enrique Vera Villares, Elena Arévalo Rodriguez, José Maria Pina López, Javier Cabeza Huertas, Diego Folch Cortés
-
Patent number: 8118260Abstract: A fitting for trimming the horizontal stabilizer of an aircraft, made of composite material, the fitting including side walls of a torsion box as well as joining elements which join the fitting to the frames of the tail fuselage of the aircraft, the side walls being joined together by a central element which includes a first end part joined to the first side wall of the fitting, a second end part joined to the second side wall of the fitting and a central part which joins together the end parts, the fitting includes end elements which are joined to the side walls on their outer face, the fitting having, owing to its greater rigidity in response to side load and vertical load stresses which tend to close the side walls, its greater integration and the simplicity of the load path, an optimum structural behavior in response to the aircraft stresses.Type: GrantFiled: April 16, 2009Date of Patent: February 21, 2012Assignee: Airbus Operations S.L.Inventor: Elena Arevalo Rodriguez
-
Patent number: 8096504Abstract: Integrated aircraft structure in composite material that comprises a skin and stringers (1), with the skin comprising a string part (5) and a basic skin (3), which structure further comprises U-shaped elements (15) each of which comprises in its turn two L-shaped sections (4a+5a and 4b+5b) together with the skin part (5), in such a way that these U-shaped elements (15) fulfill two structural functions in said structure at the same time, acting as frame feet and as skin, providing an integrated fuselage structure without rivets or joints. The invention also relates to a manufacturing process of an integrated aircraft structure in composite material.Type: GrantFiled: August 29, 2008Date of Patent: January 17, 2012Assignee: Airbus Operations, S.L.Inventors: Elena Arévalo Rodríguez, Pedro Luis Muñoz Royo
-
Publication number: 20120001024Abstract: Reinforcement structure (1) for an opening (10) in the primary structure of an aircraft, said structure comprising a skin (2), frame members (3) which are transverse with respect to the flying direction of the aircraft, and stringers (4) which are longitudinal with respect to the flying direction of the aircraft, said reinforcing structure (1) comprising: a perimetral reinforcing element (5) situated along the edge of the opening (10) and reproducing the geometrical form thereof; at least one pair of transverse reinforcing elements (6) arranged on both transverse sides of the opening (10); at least one pair of longitudinal reinforcing elements (7) arranged on both longitudinal sides of the opening (10).Type: ApplicationFiled: May 24, 2011Publication date: January 5, 2012Applicant: AIRBUS Operations S.L.Inventors: Francisco Jose Cruz Dominguez, Elena Arevalo Rodriguez
-
Publication number: 20120001023Abstract: Aircraft fuselage made out with composite material and manufacturing processes. The structure of the fuselage (11) comprises a skin (13), a plurality of frames (17) positioned transversely to the longitudinal axis (9) of the fuselage (11) and a plurality of longitudinal stiffening elements (14, 15) that can be either stringers (14) or beams (15), being the ratio between the distance (X) between frames (17) and the distance (Y) between longitudinal stiffening elements (14, 15) is less than one. If the stiffening elements are stringers (14) the manufacturing process is based on assembling the fuselage section (11) joining the skin (13) with the stringers (14) to the frames (17). If the stiffening elements are beams (15) the manufacturing process is based on joining the skin to an internal structure made up with frames (17) and beams (15).Type: ApplicationFiled: May 20, 2011Publication date: January 5, 2012Inventors: Elena Arévalo Rodríguez, Francisco José Cruz Domínguez
-
Publication number: 20110268926Abstract: Internal structure for aircraft comprising a skin (1) of composite material, some stringers (2) of composite material integrated into the interior of the aforementioned skin (1) and some frames (3) of composite material, comprising the skin (1) with some zones (4) in which its thickness (20) is greater than the thickness (10) this skin (1) has in the rest of its section, with the stringers (2) integrated into these zones (4) of the skin (1), achieving with this arrangement the isolation of the interface line (5) of the stringer (2) joint with the skin (1) from the skin (1) with thickness (10).Type: ApplicationFiled: February 16, 2011Publication date: November 3, 2011Applicant: AIRBUS Operations S.L.Inventors: Francisco Jose CRUZ DOMINGUEZ, Elena AREVALO RODRIGUEZ
-
Publication number: 20110159242Abstract: 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: ApplicationFiled: December 29, 2010Publication date: June 30, 2011Applicant: AIRBUS OPERATIONS S.L.Inventor: Elena ARÉVALO RODRÍGUEZ
-
Publication number: 20110159248Abstract: 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: ApplicationFiled: September 16, 2010Publication date: June 30, 2011Inventors: Elena ARÉVALO RODRÍGUEZ, Francisco José CRUZ DOMINGUEZ
-
Publication number: 20100264271Abstract: The invention relates to fittings (41, 71) for fixing the vertical tail stabilizer of an aircraft in an area of its rear fuselage integrally manufactured with a composite material comprising: a) a first piece (43, 73) comprising lugs (45, 45?; 75, 75?) for fixing the vertical tail stabilizer and vertical walls (47, 47?; 77, 77?) for fixing the fitting (41, 71) to the frames (7); b) at least one pair of additional pieces (49, 49?; 79, 79?) comprising horizontal walls (51, 51?; 81, 81?) for fixing the fitting (41, 71) to the skin (5). The fitting (71) for fixing with an inclined load also comprises a second pair of pieces (90, 90?) having an angular shape comprising vertical walls (93, 93?) for the fixing with the lugs (75, 75?). The invention also relates to processes for assembling these fittings (41, 71).Type: ApplicationFiled: February 26, 2010Publication date: October 21, 2010Applicant: AIRBUS OPERATIONS S.L.Inventors: Diego Folch Cortés, Enrique Vera Villares, Javier Cabeza Huertas, José María Pina López, Elena Arévalo Rodríguez
-
Publication number: 20100155532Abstract: 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: ApplicationFiled: February 19, 2009Publication date: June 24, 2010Inventors: Manuel Ariza Martin, Elena Arevalo Rodriguez, Francisco Jose Cruz Dominguez
-
Publication number: 20100108803Abstract: Fitting (30) for trimming the horizontal stabilizer (1a) of an aircraft, made of composite material, said fitting (30) comprising side walls (2a and 2b) of a torsion box as well as joining elements (3a, 3b) which join the fitting (30) to the frames of the tail fuselage (1) of the aircraft, said side walls (2a, 2b) being joined together by means of a central element (4) which comprises a first end part (4a) joined to the first side wall (2a) of the fitting (30), a second end part (4b) joined to the second side wall (2b) of the fitting (30) and a central part (4c) which joins together said end parts (4a, 4b), the fitting (30) moreover comprising end elements (5a, 5b) which are joined to said side walls (2a, 2b) on their outer face, said fitting (30) having, owing to its greater rigidity in response to side load and vertical load stresses which tend to close the side walls (2a, 2b), its greater integration and the simplicity of the load path, an optimum structural behaviour in response to the aircraft stresses.Type: ApplicationFiled: April 16, 2009Publication date: May 6, 2010Applicant: AIRBUS ESPANA S.L.Inventor: Elena AREVALO RODRIGUEZ
-
Publication number: 20090283638Abstract: Integrated aircraft structure in composite material that comprises a skin and stringers (1), with the skin comprising a skin part (5) and a basic skin (3), and said structure further comprises U-shaped elements (15) each of which comprises in its turn two L-shaped sections (4a+5a and 4b+5b) together with the skin part (5), in such a way that these U-shaped elements (15) fulfil two structural functions in said structure at the same time, acting as frame feet and as skin, providing an integrated fuselage structure without rivets or joints. The invention also relates to a manufacturing process of an integrated aircraft structure in composite material.Type: ApplicationFiled: August 29, 2008Publication date: November 19, 2009Inventors: Elena AREVALO RODRIGUEZ, Pedro Luis MUNOZ ROYO
-
Patent number: 7597772Abstract: The present invention relates to a tubular-shaped component (19) for an aeronautical fuselage made of composite materials comprising an outer skin (1) without joints having a cylindrical or cylindrical-conical shape, a plurality of stiffeners or stringers (2) longitudinally arranged in said outer skin (1) and a plurality of anchoring elements (3) for anchoring other elements to subsequently be incorporated transversally arranged between said stiffeners or stringers (2). The invention also comprises a jig (18) comprising a support body (12) and a plurality of panels (9) that can shift between an extended position (10) and a retracted position (10?) in both directions and a process for manufacturing said component (19) in the last step of which once the tubular component (19) is formed and cured, it is separated from the jig (18) by means of a longitudinal movement after the shifting of those elements of the jig (18) preventing it, and particularly the panels (9) that can be shifted.Type: GrantFiled: October 30, 2006Date of Patent: October 6, 2009Assignee: Airbus Espana, S.L.Inventors: Alberto Ramon Martinez Cerezo, Elena Arevalo Rodriguez, Jorge Juan Galiana Blanco, Francisco Javier Jordan Carnicero
-
Publication number: 20090217529Abstract: The present invention relates to a tubular-shaped component (19) for an aeronautical fuselage made of composite materials comprising an outer skin (1) without joints having a cylindrical or cylindrical-conical shape, a plurality of stiffeners or stringers (2) longitudinally arranged in said outer skin (1) and a plurality of anchoring elements (3) for anchoring other elements to subsequently be incorporated transversally arranged between said stiffeners or stringers (2). The invention also comprises a jig (18) comprising a support body (12) and a plurality of panels (9) that can shift between an extended position (10) and a retracted position (10?) in both directions and a process for manufacturing said component (19) in the last step of which once the tubular component (19) is formed and cured, it is separated from the jig (18) by means of a longitudinal movement after the shifting of those elements of the jig (18) preventing it, and particularly the panels (9) that can be shifted.Type: ApplicationFiled: October 30, 2006Publication date: September 3, 2009Inventors: Alberto Ramon Martinez Cerezo, Elena Arevalo Rodriguez, Jorge Juan Galiana Blanco, Francisco Javier Jordan Carnicero