Patents by Inventor Alberto Dei CASTELLI
Alberto Dei CASTELLI 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: 11643199Abstract: Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.Type: GrantFiled: May 6, 2020Date of Patent: May 9, 2023Assignee: EVE UAM, LLCInventors: Adilson Melo, Alberto Dei Castelli, Fabio Zaroni, Felipe Nahime Cursino, Fernando Rodrigues Vianna, Flavia Renata Dantas Alves Silva, Geraldo Carvalho, Igor Miranda Rodrigues, Julio Cesar Graves, Luiz Antonio Madeira, Jr., Luiz Felipe Ribeiro Valentini, Rafael Desideri de Freitas, Rafael Estefano Reis Cleto, Ricardo Takeshi Demizu, Rodrigo Takashi Lourenco Kawasaki, Thalerson Augusto Mortari Alves, Vinicius Magalhaes Cunha, Yasser Mahmud Abdallah
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Patent number: 11383830Abstract: Vertical take-off and landing (VTOL) aircraft include a fuselage having a center of gravity (CG) and defining mutually orthogonal X-, Y- and Z-axes. An even number of positionally mirror imaged port and starboard side rotors are provided laterally of the fuselage in spaced relationship to a plane established by the XZ axes while an even number of fuselage rotors are positioned along an X-axis centerline of the fuselage. Improved stability during failure of an engine/motor/rotor is achieved by causing one-half of the side rotors to rotate in one direction about the Z-axis and a remaining one-half of the side rotors rotate in a counter direction relative thereto, while one-half of the fuselage rotors rotate in one direction about the Z-axis and a remaining one-half of the fuselage rotors rotated in a counter direction relative thereto.Type: GrantFiled: April 23, 2019Date of Patent: July 12, 2022Assignee: EVE UAM, LLCInventors: Julio Cesar Graves, Alberto Dei Castelli, Jose Roberto Ferreira de Camargo Clark Reis, Rodrigo Takashi Lourenço Kawasaki
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Patent number: 11312351Abstract: A hovercraft including imaginary longitudinal, transverse and vertical axes; a propulsion system (12), configured to generate airflow; a base (50) and, a skirt (13) wherein the skirt (13) further including air permeable regions (130) and at least two set of outflow nozzles (220); wherein the air permeable regions (130) and the set of outflow nozzles (20, 21) are in fluid communication; wherein each set of nozzles (20, 21) comprises, at least, one outflow nozzle (22), said outflow nozzle (22) including two opposing ends, a first end (221) and a second end (222); the hovercraft further including actuating means (30) suitable to control the opening of at least one end (221 or 222) of the nozzles (22) managing the passage of airflow through the end (221 or 222). The technical features and functionalities described herein are applicable to the field of hovercrafts. More particularly, to controllable outflow nozzles and controlling systems for hovercrafts.Type: GrantFiled: November 6, 2017Date of Patent: April 26, 2022Inventor: Alberto Dei Castelli
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Publication number: 20200354048Abstract: Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.Type: ApplicationFiled: May 6, 2020Publication date: November 12, 2020Inventors: Adilson MELO, Alberto Dei CASTELLI, Fabio ZARONI, Felipe Nahime CURSINO, Fernando Rodrigues VIANNA, Flavia Renata Dantas Alves SILVA, Geraldo CARVALHO, Igor Miranda RODRIGUES, Julio Cesar GRAVES, Luiz Antonio Madeira JUNIOR, Luiz Felipe Ribeiro VALENTINI, Rafael Desideri de FREITAS, Rafael Estefano Reis CLETO, Ricardo Takeshi DEMIZU, Rodrigo Takashi Lourenco KAWASAKI, Thalerson Augusto Mortari ALVES, Vinicius Magalhaes CUNHA, Yasser Mahmud ABDALLAH
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Publication number: 20200298815Abstract: A hovercraft including imaginary longitudinal, transverse and vertical axes; a propulsion system (12), configured to generate airflow; a base (50) and, a skirt (13) wherein the skirt (13) further including air permeable regions (130) and at least two set of outflow nozzles (220); wherein the air permeable regions (130) and the set of outflow nozzles (20, 21) are in fluid communication; wherein each set of nozzles (20, 21) comprises, at least, one outflow nozzle (22), said outflow nozzle (22) including two opposing ends, a first end (221) and a second end (222); the hovercraft further including actuating means (30) suitable to control the opening of at least one end (221 or 222) of the nozzles (22) managing the passage of airflow through the end (221 or 222). The technical features and functionalities described herein are applicable to the field of hovercrafts. More particularly, to controllable outflow nozzles and controlling systems for hovercrafts.Type: ApplicationFiled: November 6, 2017Publication date: September 24, 2020Inventor: Alberto Dei Castelli
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Publication number: 20190329880Abstract: Vertical take-off and landing (VTOL) aircraft include a fuselage having a center of gravity (CG) and defining mutually orthogonal X-, Y- and Z-axes. An even number of positionally mirror imaged port and starboard side rotors are provided laterally of the fuselage in spaced relationship to a plane established by the XZ axes while an even number of fuselage rotors are positioned along an X-axis centerline of the fuselage. Improved stability during failure of an engine/motor/rotor is achieved by causing one-half of the side rotors to rotate in one direction about the Z-axis and a remaining one-half of the side rotors rotate in a counter direction relative thereto, while one-half of the fuselage rotors rotate in one direction about the Z-axis and a remaining one-half of the fuselage rotors rotated in a counter direction relative thereto.Type: ApplicationFiled: April 23, 2019Publication date: October 31, 2019Inventors: Julio Cesar GRAVES, Alberto DEI CASTELLI, Jose Roberto Ferreira de CAMARGO CLARK REIS, Rodrigo Takashi Lourenço KAWASAKI
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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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Patent number: 10301030Abstract: It is described a movable pylon, associated with a lower portion of aircraft wing and with an aircraft engine to change the height of this engine between a flying position and a ground position, the movable pylon comprising: a main unique structure formed by a first movable structure pivoted to a second fixed structure, the first movable structure associated with the engine, the second fixed structure associated with the wing, and a pivot mechanism connecting the first movable structure to at least one point on the wing.Type: GrantFiled: October 14, 2014Date of Patent: May 28, 2019Assignee: EMBRAER S.A.Inventor: Alberto Dei Castelli
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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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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: 20160368611Abstract: It is described a movable pylon, associated with a lower portion of aircraft wing and with an aircraft engine to change the height of this engine between a flying position and a ground position, the movable pylon comprising: a main unique structure formed by a first movable structure pivoted to a second fixed structure, the first movable structure associated with the engine, the second fixed structure associated with the wing, and a pivot mechanism connecting the first movable structure to at least one point on the wing.Type: ApplicationFiled: October 14, 2014Publication date: December 22, 2016Inventor: Alberto Dei CASTELLI
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Patent number: D914171Type: GrantFiled: May 10, 2019Date of Patent: March 23, 2021Assignee: EMBRAER S.A.Inventors: Adilson Melo, Alberto Dei Castelli, Fabio Zaroni, Felipe Nahime Cursino, Fernando Rodrigues Vianna, Flavia Renata Dantas Alves Silva, Geraldo Carvalho, Igor Miranda Rodrigues, Julio Cesar Graves, Luiz Antonio Madeira Junior, Luiz Felipe Ribeiro Valentini, Rafael Desideri de Freitas, Rafael Estefano Reis Cleto, Ricardo Takeshi Demizu, Rodrigo Takashi Lourenco Kawasaki, Thalerson Augusto Mortari Alves, Vinicius Magalhaes Cunha, Yasser Mahmud Abdallah