Patents by Inventor Clovis Augusto Eca Ferreira
Clovis Augusto Eca Ferreira 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).
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Patent number: 10450081Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.Type: GrantFiled: November 30, 2018Date of Patent: October 22, 2019Assignee: EMBRAER S.A.Inventors: Julio Antonio Beltrami Da Silva, Clovis Augusto Eça Ferreira, Wanderley Montoro, Alberto Dei Castelli, José Darci Flor Junior, Marcelo Nogueira, Cleber Soares
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Publication number: 20190100325Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.Type: ApplicationFiled: November 30, 2018Publication date: April 4, 2019Inventors: Julio Antonio Beltrami DA SILVA, Clovis Augusto Eça FERREIRA, Wanderley MONTORO, Alberto Dei CASTELLI, José Darci FLOR, Marcelo NOGUEIRA, Cleber SOARES
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Patent number: 10144525Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.Type: GrantFiled: September 24, 2015Date of Patent: December 4, 2018Assignee: EMBRAER S.A.Inventors: Julio Antonio Beltrami Da Silva, Clovis Augusto Eça Ferreira, Wanderley Montoro, Alberto Dei Castelli, José Darci Flor, Jr., Marcelo Nogueira, Cleber Soares
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Patent number: 9868539Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box. The upper pylon connection member and the lower pylon connection box respectively define opposed lower and upper mounting surfaces which establish a mounting plane that slopes downwardly and rearwardly relative to aircraft travel direction. At least one connector assembly connects the upper pylon connection member and a lower pylon connection box to one another at the opposed respective lower and upper mounting surfaces thereof.Type: GrantFiled: September 24, 2015Date of Patent: January 16, 2018Assignee: EMBRAER S.A.Inventors: Alberto Dei Castelli, Clovis Augusto Eça Ferreira, Wanderley Montoro, Aldemiro Lorenzini Filho, Carlos Alberto Bones, Jr., Juliano De Oliveira
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Patent number: 9656738Abstract: An aircraft wing is provided having a spanwise wing spar which includes a one-piece upright central web extending in a spanwise direction between inboard and outboard ends of the wing spar, and a plurality of contiguously adjacent wing spar sections. At least a first wing spar section includes at least one upper and lower spar chord which is unitarily formed as a one-piece structure with upper and lower ends of the upright central web, respectively, while at least a second wing spar section includes at least one upper and lower spar chord which is a separate structural element integrally fixed to the upper and lower ends of the upright central web, respectively.Type: GrantFiled: July 6, 2015Date of Patent: May 23, 2017Assignee: EMBRAER S.A.Inventors: Yvan Bovolenta Murta, Renato Campos da Silveira, Clovis Augusto Eça Ferreira, Wanderley Montoro
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Publication number: 20170088279Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box. The upper pylon connection member and the lower pylon connection box respectively define opposed lower and upper mounting surfaces which establish a mounting plane that slopes downwardly and rearwardly relative to aircraft travel direction. At least one connector assembly connects the upper pylon connection member and a lower pylon connection box to one another at the opposed respective lower and upper mounting surfaces thereof.Type: ApplicationFiled: September 24, 2015Publication date: March 30, 2017Inventors: Alberto Dei CASTELLI, Clovis Augusto Eça FERREIRA, Wanderley MONTORO, Aldemiro Lorenzini FILHO, Carlos Alberto BONES, JR., Juliano DE OLIVEIRA
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Publication number: 20170088278Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.Type: ApplicationFiled: September 24, 2015Publication date: March 30, 2017Inventors: Julio Antonio Beltrami DA SILVA, Clovis Augusto Eça FERREIRA, Wanderley MONTORO, Alberto Dei CASTELLI, José Darci FLOR, JR., Marcelo NOGUEIRA, Cleber SOARES
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Publication number: 20170008611Abstract: An aircraft wing is provided having a spanwise wing spar which includes a one-piece upright central web extending in a spanwise direction between inboard and outboard ends of the wing spar, and a plurality of contiguously adjacent wing spar sections. At least a first wing spar section includes at least one upper and lower spar chord which is unitarily formed as a one-piece structure with upper and lower ends of the upright central web, respectively, while at least a second wing spar section includes at least one upper and lower spar chord which is a separate structural element integrally fixed to the upper and lower ends of the upright central web, respectively.Type: ApplicationFiled: July 6, 2015Publication date: January 12, 2017Inventors: Yvan Bovolenta MURTA, Renato Campos da SILVEIRA, Clovis Augusto Eça FERREIRA, Wanderley MONTORO
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Patent number: 9540095Abstract: There is described an aerodynamic surface drive mechanism (20) containing at least a drive combination (50, 50?), each drive combination (50, 50?) comprising a fixed element (21) associated to a fixed aircraft structure and a first mobile component (22) connected pivotably by a first end to the fixed element (21) by way of an articulation axis (E) and associated to an actuator (30) by an opposite end, the aerodynamic surface drive mechanism (20) further comprises a second mobile component (23) rotationally associated to the first mobile component (22) by way of primary swivel joints (24, 24?) linearly disposed along a vertical axis (Y) and rotationally connected to the aerodynamic surface (40) by way of secondary swivel joints (25, 25?) linearly disposed along a horizontal axis (Z); the first mobile component (22) and the second mobile component (23) simultaneously moving the aerodynamic surface (40) linearly and rotatively by means of the actuator (30) and of the primary swivel joints (24, 24?) and secondaryType: GrantFiled: September 24, 2014Date of Patent: January 10, 2017Assignee: EMBRAER S.A.Inventors: Clóvis Augusto Eça Ferreira, Israel Da Silva
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Publication number: 20150083854Abstract: There is described an aerodynamic surface drive mechanism (20) containing at least a drive combination (50, 50?), each drive combination (50, 50?) comprising a fixed element (21) associated to a fixed aircraft structure and a first mobile component (22) connected pivotably by a first end to the fixed element (21) by way of an articulation axis (E) and associated to an actuator (30) by an opposite end, the aerodynamic surface drive mechanism (20) further comprises a second mobile component (23) rotationally associated to the first mobile component (22) by way of primary swivel joints (24, 24?) linearly disposed along a vertical axis (Y) and rotationally connected to the aerodynamic surface (40) by way of secondary swivel joints (25, 25?) linearly disposed along a horizontal axis (Z); the first mobile component (22) and the second mobile component (23) simultaneously moving the aerodynamic surface (40) linearly and rotatively by means of the actuator (30) and of the primary swivel joints (24, 24?) and secondaryType: ApplicationFiled: September 24, 2014Publication date: March 26, 2015Inventors: Clóvis Augusto Eça FERREIRA, Israel Da Silva
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Patent number: 8844871Abstract: Aircraft fuselage structures have reinforcement members in the vicinity of the stringer openings formed in frame members and are rigidly lap joined to a surface region of the frame members by a friction stir weld region. Such aircraft fuselage structural components may thus be provided with plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, and plural longitudinally oriented stringers each being positioned within a respective one of the stringer holes of the frame member. The reinforcement members are lap joined to corresponding surfaces of frame members in the vicinity of the stringer holes such that the reinforcement members are joined rigidly to the corresponding surfaces of the frame members by a friction stir weld region.Type: GrantFiled: October 4, 2012Date of Patent: September 30, 2014Assignee: Embraer S.A.Inventors: Fernando Ferreira Fernandez, Sadao Takanashi, Lucio Camargo Fortes, Marcio Cruz, Marcelo Galvão do Prado, Clovis Augusto Eça Ferreira, José Donizette Aguiar
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Patent number: 7967250Abstract: An aircraft fuselage assembly of basic construction in composite materials employs metallic frames with reduced quantity of metallic shear ties attached to the composite stiffened skin, formed by two or more longitudinal panels, spliced with longitudinal metallic splice members. Typically, the latitudinal metallic frame members are fastened to the inward outstanding flange portion of the composite stringers which are in turn integrated to the skin. As such, the frame members are spaced from (floating over) the fuselage skin. An electrical path may thus be established so as to protect the fuselage structure against the impact of electrical discharges commonly encountered in the atmosphere by providing metallic shear ties interconnecting the frame and splice members so as to span the space therebetween.Type: GrantFiled: May 12, 2008Date of Patent: June 28, 2011Assignee: EMBRAER—Empresa Brasileira de AeronáuticaInventors: Fabiano Lobato, Clóvis Augusto Eça Ferreira, José Donizette Aguiar, Lucio Camargo Fortes, Sadao Takanashi
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Publication number: 20090266936Abstract: Aircraft fuselage structures have reinforcement members in the vicinity of the stringer openings formed in frame members and are rigidly lap joined to a surface region of the frame members by a friction stir weld region. Such aircraft fuselage structural components may thus be provided with plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, and plural longitudinally oriented stringers each being positioned within a respective one of the stringer holes of the frame member. The reinforcement members are lap joined to corresponding surfaces of frame members in the vicinity of the stringer holes such that the reinforcement members are joined rigidly to the corresponding surfaces of the frame members by a friction stir weld region.Type: ApplicationFiled: April 29, 2008Publication date: October 29, 2009Inventors: Fernando Ferreira Fernandez, Sadao Takanashi, Lucio Camargo Fortes, Marcio Cruz, Marcelo Galvao do Prado, Clovis Augusto Eca Ferreira, Jose Donizette Aguiar