Patents by Inventor Ierko De Magalhães Gomes

Ierko De Magalhães Gomes 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: 20210276693
    Abstract: A thrust propeller variable pitch actuator is controlled by a governor that uses propeller pitch as a variable to increase or decrease torque—not to maintain the propeller speed or RPM but instead to maintain certain established electric current supplied to rotate the thrust propeller.
    Type: Application
    Filed: February 24, 2021
    Publication date: September 9, 2021
    Inventor: Ierko de MAGALHÃES GOMES
  • Patent number: 10227138
    Abstract: An aircraft compensates for asymmetry of engine failure by drawing part of the energy produced by the still-operating engine to generate thrust at the tip of the opposite wing. For example, the left engine drives its own thrust on the left wing, but a portion of the energy the left engine produces is delivered at a propeller at the tip of right wing. Similarly, the right engine drives its own thrust on the right wing, but a portion of the energy the right engine produces is delivered at a propeller at the tip of the left wing. In this way, every pair of engines and opposite tip thrust generators are intrinsically balanced. In the event of one engine failure, no yaw moment will be noticed.
    Type: Grant
    Filed: March 4, 2016
    Date of Patent: March 12, 2019
    Assignee: Embraer S.A.
    Inventor: Ierko De Magalhães Gomes
  • Publication number: 20170253342
    Abstract: An aircraft compensates for asymmetry of engine failure by drawing part of the energy produced by the still-operating engine to generate thrust at the tip of the opposite wing. For example, the left engine drives its own thrust on the left wing, but a portion of the energy the left engine produces is delivered at a propeller at the tip of right wing. Similarly, the right engine drives its own thrust on the right wing, but a portion of the energy the right engine produces is delivered at a propeller at the tip of the left wing. In this way, every pair of engines and opposite tip thrust generators are intrinsically balanced. In the event of one engine failure, no yaw moment will be noticed.
    Type: Application
    Filed: March 4, 2016
    Publication date: September 7, 2017
    Inventor: Ierko DE MAGALHÃES GOMES
  • Patent number: 8322654
    Abstract: Galley units are provided having a moveable galley structure in the interior aircraft cabin. During passenger ingress/egress and during certain phases of the aircraft's flight (e.g., take-off and landing), the galley structure may be moved so as to be laterally adjacent the main cabin door and thereby provide access to the door. During other phases of the aircraft's flight (e.g., during cruise flight at altitude), the galley structure may be moved laterally so as to cover the main cabin door and thereby provide enhanced acoustic and/or thermal insulation in the main cabin door area. The space vacated by the moveable galley structure may thus expose other galley structures and/or equipment. An aircraft which includes such an aircraft galley unit and methods to achieve acoustic and/or thermal insulation for an aircraft cabin door using such an aircraft galley unit are also provided.
    Type: Grant
    Filed: November 2, 2009
    Date of Patent: December 4, 2012
    Assignee: Embraer S.A.
    Inventors: Ierko De Magalhães Gomes, Jose Celso Bustamante Coura
  • Patent number: 7984880
    Abstract: Rudder assist mechanisms and methods are capable of being operably connected to an aircraft's rudder control system. The rudder assist mechanisms most preferably have over-the-center spring biasing functions so as to cause either substantially no spring force (i.e., when the linkage is over the spring-bias center) or substantially all spring force (i.e., when the linkage is left or right of the spring-bias center) to be exerted on the rudder control system. The rudder assist mechanism may include a control spring assembly, and a linkage assembly which operably connects the control spring assembly to the rudder control assembly. The linkage assembly is moveable operably between a null position wherein substantially no spring force of the control spring assembly is transferred to the rudder control system by the linkage assembly, and right and left spring-biased positions wherein right and left spring forces of the control spring assembly are transferred to the rudder control system, respectively.
    Type: Grant
    Filed: October 9, 2007
    Date of Patent: July 26, 2011
    Assignee: Embraer-Empresa Brasileira de Aeronautica S.A.
    Inventor: Ierko de Magalhaes Gomes
  • Publication number: 20110101160
    Abstract: Galley units are provided having a moveable galley structure in the interior aircraft cabin. During passenger ingress/egress and during certain phases of the aircraft's flight (e.g., take-off and landing), the galley structure may be moved so as to be laterally adjacent the main cabin door and thereby provide access to the door. During other phases of the aircraft's flight (e.g., during cruise flight at altitude), the galley structure may be moved laterally so as to cover the main cabin door and thereby provide enhanced acoustic and/or thermal insulation in the main cabin door area. The space vacated by the moveable galley structure may thus expose other galley structures and/or equipment. An aircraft which includes such an aircraft galley unit and methods to achieve acoustic and/or thermal insulation for an aircraft cabin door using such an aircraft galley unit are also provided.
    Type: Application
    Filed: November 2, 2009
    Publication date: May 5, 2011
    Applicant: EMBRAER - EMPRESA BRASILEIRA DE AERONAUTICA S.A.
    Inventors: Ierko De Magalhães GOMES, Jose Celso Bustamante COURA
  • Publication number: 20090090816
    Abstract: Rudder assist mechanisms and methods are capable of being operably connected to an aircraft's rudder control system. The rudder assist mechanisms most preferably have over-the-center spring biasing functions so as to cause either substantially no spring force (i.e., when the linkage is over the spring-bias center) or substantially all spring force (i.e., when the linkage is left or right of the spring-bias center) to be exerted on the rudder control system. The rudder assist mechanism may include a control spring assembly, and a linkage assembly which operably connects the control spring assembly to the rudder control assembly. The linkage assembly is moveable operably between a null position wherein substantially no spring force of the control spring assembly is transferred to the rudder control system by the linkage assembly, and right and left spring-biased positions wherein right and left spring forces of the control spring assembly are transferred to the rudder control system, respectively.
    Type: Application
    Filed: October 9, 2007
    Publication date: April 9, 2009
    Applicant: EMBRAER - Empresa Brasileira de Aeronautica S.A.
    Inventor: Ierko de Magalhaes GOMES