Patents Assigned to Embraer S.A.
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Patent number: 8490923Abstract: Portable vehicular hoist systems include a truss assembly having a joist member with forward and rearward ends, a pair of rafter members each having upper and lower ends, and a forward connection assembly for connecting the upper ends of the rafter members to the forward end of the joist member to allow for relative pivotal articulated movements therebetween. The rafter members may thus be pivotally moved between a stowed condition wherein the rafter members are oriented generally parallel to the joist member and an operative position wherein the rafter members extend downwardly and laterally outwardly from the joist member. A hoist assembly may be provided so as to be connectable to the joist member of the truss assembly to be supported thereby. The rearward end of the joist member and the lower ends of the rafter members may be removably attached to respective connection lugs rigidly fixed to a vehicle's structure, e.g., an aircraft fuselage at an opening therein.Type: GrantFiled: December 22, 2009Date of Patent: July 23, 2013Assignee: Embraer S.A.Inventors: Thiago de Almeida Bosqueiro, Gustavo Aparecido de Lima Moreira, Vinícius Visacro
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Publication number: 20130180096Abstract: Self-aligning couplers and methods for aligning superposed surfaces include a circular and semi-spherical base formed on a first surface, a fastening element perpendicularly passing through the circular and semi-spherical base and associated to a second surface, and at least a semi-spherical insert disposed on the circular and semi-spherical base and concentric to the fastening element. The semi-spherical insert is cooperative with the circular and semi-spherical base and the fastening element for the self-alignment and superposed fastening of the first and second surfaces.Type: ApplicationFiled: December 21, 2012Publication date: July 18, 2013Applicant: EMBRAER S.A.Inventor: EMBRAER S.A.
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Publication number: 20130168502Abstract: Diverter assemblies for aircraft air inlets include a diverter structure at least substantially surrounding the air inlet, and a fairing mounted to an upper edge of the diverter structure forwardly of the air inlet.Type: ApplicationFiled: December 21, 2012Publication date: July 4, 2013Applicant: EMBRAER S.A.Inventor: EMBRAER S.A.
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Publication number: 20130169807Abstract: To create an environment in which the passenger has the same emotion, feel and visual experience that a pilot has with regard to freedom of flight and proximity to the exterior of the aircraft and where passengers have the impression that they are looking out of an actual panoramic window, a “virtual window” includes internal and the external aspects of a real window. The internal part can comprise a folded or flexible high resolution color display that conforms to the internal profile of the aircraft fuselage as if it were an actual window. The external part comprises a paint scheme that is indistinguishable from an actual window and which is placed on the outside of the aircraft fuselage in registry with the conformal display in the aircraft's interior.Type: ApplicationFiled: November 30, 2012Publication date: July 4, 2013Applicant: EMBRAER S.A.Inventor: EMBRAER S.A.
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Publication number: 20130166458Abstract: Structural analysis automation allows the implementation of more detailed or accurate analysis methodology that reflects the actual behavior of the damaged or repaired structure and consequently improves the resulting damage disposition for example by Increasing the allowable damages and structural repairs applicability, increasing the allowable damage limits causing the reduction of unnecessary installation of structural repairs, optimizing repairs and increasing fly-by periods and inspection intervals.Type: ApplicationFiled: December 22, 2011Publication date: June 27, 2013Applicant: EMBRAER S.A.Inventors: Cassio Wallner, Paulo Anchieta da Silva, Ricardo Rogulski, Ricardo Pinheiro Rulli, Tomaz Lazanha
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Patent number: 8453968Abstract: A retractable optical sensor system includes a sensor body (e.g., an electro-optical/infrared (EO/IR) remote sensor) connected to a sensor support structure that is actuated by an actuator. The sensor support structure accomplishes angular movement whose turning point is located in an end that is mounted to an articulation support. A bulkhead support is fastened to the aircraft structure. The actuator is electrically or hydraulically actuated and has an end united to a support member which is fastened to the aircraft structure. The opposite end of the actuator is connected for articulation to the sensor support structure so as to cause angular movement thereof. Articulation of the sensor support structure causes the sensor body to extend/retract while simultaneously causing the fairing door to be raised/lowered, respectively.Type: GrantFiled: March 27, 2008Date of Patent: June 4, 2013Assignee: Embraer S.A.Inventor: Mario Sergio Dias Ferraz
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Publication number: 20130138274Abstract: A longitudinal control law is designed to optimize the flying qualities when aircraft is set to approach configuration, i.e. when the flap lever is set to the landing position and landing gears are locked down. Under such circumstances, the effort of trimming the aircraft speed can be extremely reduced by the usage of a momentary on-off switch or other control in the sidestick, instead of or in addition to a conventional trim up-down switch, making easier the task of airspeed selection by the pilot. This control law provides excellent handling qualities during approach and landing, with the benefit of not needing or using radio altimeter information in safety-critical applications.Type: ApplicationFiled: November 28, 2011Publication date: May 30, 2013Applicant: EMBRAER S.A.Inventors: Fabrício Reis Caldeira, Marcos Vinicius Campos, Reneu Luiz Andrioli Junior, Wagner de Oliveira Carvalho, Dagfinn Gangsaas, Eduardo Camelier, Daniel Siqueira, Lucas Rubiano
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Publication number: 20130133469Abstract: Sidestick controller grips are provided with a base, an elongate column grip extending upwardly from the base, a head at an upper end portion of the grip column, and a thumb rest surface extending laterally and upwardly relative to the column grip. The thumb rest surface may be supported by a concave outwardly extending support wall which joins the thumbrest surface at a generally serpentine edge which may extend generally outwardly convexly from a lower region thereof at the column grip to a convex apex region, and then extends from the apex region generally upwardly and concavely to an upper region thereof at the head.Type: ApplicationFiled: November 28, 2011Publication date: May 30, 2013Applicant: EMBRAER S.A.Inventors: Hans Jorg REY, Luiz Fernando Silva de CASTRO PAIVA, Celso Aparecido Cruz GUEIROS, Rogério de CERQUEIRA LARIO, Bruno Kimura CASTANHA
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Publication number: 20130043346Abstract: 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: October 4, 2012Publication date: February 21, 2013Applicant: EMBRAER S.A.Inventor: EMBRAER S.A.
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Patent number: 8371523Abstract: A system that acts on a rudder (L) having its stop parts commanded or moved by an actuator (A) is described. The rudder system comprises a reversible mechanical system with movable stop parts working based on control/command signals, having stop parts (M, M?) inside of the field of movement of the actuator (A), interfering in the movement of said actuator; the mentioned control signals are based on informations of the aircraft such as traction of the engines or other signal from each engine (pressure, temperature or axis rotation speed); flight speed (“airspeed”); altitude; skidding angle; aircraft on the ground.Type: GrantFiled: September 25, 2007Date of Patent: February 12, 2013Assignee: Embraer S.A.Inventors: Edwin José Meinberg Macedo, Leonardo Cavanha Almeida
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Patent number: 8336820Abstract: Structures, systems and methods provide a load-bearing aircraft flooring within an aircraft's fuselage. Load-supporting aircraft flooring systems preferably are provided with a longitudinally separated series of transverse bridges having an upper doubler flange which defines latitudinally separated upper openings, and a latitudinally separated series of beams which include an upper flange and a pair of separated depending web flanges received within respective upper openings of transverse bridges. The upper flanges and web flanges of the beams may thus be connected to the transverse bridges so as to support aircraft flooring panels connected to the beams. Seat tracks for attaching aircraft seats and/or other interior aircraft structures/monuments are preferably fixed to the upper flanges of the beams coincident with its longitudinal axis.Type: GrantFiled: October 27, 2008Date of Patent: December 25, 2012Assignee: Embraer S.A.Inventors: Silvio Luiz Francisco Osorio, Erich Robert Schaay, Marcos Dressler Arantes
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Patent number: 8322654Abstract: 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: GrantFiled: November 2, 2009Date of Patent: December 4, 2012Assignee: Embraer S.A.Inventors: Ierko De Magalhães Gomes, Jose Celso Bustamante Coura
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Patent number: 8306778Abstract: A method and system for monitoring and predicting the health of electro-mechanical systems and components includes collecting data for a fixed pattern of actuation of such system or component. This data is used to build statistical models that correspond to a normal state of the system or component. New measurements are compared to this model in order to monitor the health of the system or component. The comparison can be made using a distance calculation. The combination of new measurements with historical data provides the prediction for future health states of the system or component.Type: GrantFiled: December 11, 2009Date of Patent: November 6, 2012Assignee: Embraer S.A.Inventors: Bruno Paes Leao, Joao Paulo Pordeus Gomes
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Patent number: 8261959Abstract: Friction stir welding equipment control force spindle for mounting in an orbital head housing uses a coaxial sensor to measure downforce. Simultaneously, an axial electrical actuator is controlled to dynamically correct the axial tool position during the welding, by a direct axial force system control, in order to maintain controlled downforce according to parameters previously set, based on numerical control. The equipment also sets up, monitors and controls spindle rotation speed, welding speed, acceleration speed and downforce using for example closed loop control functions. A laser system may scan the backing surface before welding and correct original tool path, in order to get an offset tool path. A precision alarm system may provide safe welding while preventing the tool from colliding with the backing surface.Type: GrantFiled: September 15, 2010Date of Patent: September 11, 2012Assignee: Embraer S.A.Inventors: Marcio Fernando Cruz, Gustavo Freitas, Hamilton Zanini, Jefferson Adriano da Costa, Robson Fernando de Oliverira Pereira, Edson Pereira, Fernando Ferreira Fernandez, Mauricio Andena
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Patent number: 8226040Abstract: Fuel transference between aircraft fuel tanks, disposed in different locations, is used to maintain the aircraft Center of Gravity close to the aft limit of the certified Center of Gravity versus weight envelope. Continuous fuel transfer decreases the control band thus enhancing aircraft performance.Type: GrantFiled: August 25, 2008Date of Patent: July 24, 2012Assignee: Embraer S.A.Inventor: Rubens Domecildes Neto
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Patent number: 8167243Abstract: Systems and methods achieve an optical effect of cabin enlargement of a passenger vehicle. The optical effect creates a visual impression of a higher cabin when viewed from the forward part of the cabin space looking aft, and a wider cabin space when viewed from the aft part of the cabin space looking forward. In preferred forms, a series of alternating interdigitated trapezoidal starboard and port headliner modules are disposed adjacent to the cabin headliner. The headliner modules are also preferably arcuately curved about a central elongate axis of the passenger cabin.Type: GrantFiled: September 29, 2008Date of Patent: May 1, 2012Assignee: Embraer S.A.Inventor: Carlos Eduardo De Carvalho
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Patent number: 8165733Abstract: A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protections thru the automatic elevator command if the flight vehicle is close to its envelope limits. The exemplary illustrative non-limiting implementation herein provides automatic protections in order to protect the flight vehicle from low speeds, high attitude, stalls and buffetings.Type: GrantFiled: September 4, 2007Date of Patent: April 24, 2012Assignee: Embraer S.A.Inventors: Fabricio Reis Caldeira, Dagfinn Gangsaas, Alvaro Vito Polati de Souza, Eduardo da Saiva Martins, Marco Tulio Sguerra Vita, Jose Marcio Vieira Dias Filho, Marcos Vinicius Campos, Emerson Freitas
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Patent number: 8123167Abstract: Aircraft empennage structures have impact resistance satisfying transport aircraft certification requirements (for example, FAR part 25 and/or other international certification requirements). The structures may be specifically embodied in leading edge structures that are preferably in the form of one-piece components formed from fiber-reinforced composite materials (e.g., reinforcement fibers such as glass fibers, aramid fibers and/or carbon fibers embedded in a polymeric matrix such as an epoxy resin). The leading edge structures will most preferably include an arcuate skin and longitudinally extending internal reinforcement which is generally Y-shaped and includes a planar rib element and a pair of planar divergent reinforcement arms. The rib element may be positioned so as to be coplanar with a longitudinal bisecting plane of the leading edge structure.Type: GrantFiled: December 15, 2008Date of Patent: February 28, 2012Assignee: Embraer S.A.Inventors: Franco Olmi, Luiz André Romariz
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Patent number: 8118265Abstract: Aircraft wings are provided with aerodynamic devices that improve the wing's low airspeed aerodynamics. In preferred embodiments, the aircraft wings include a slat operatively positioned at the wing's leading edge for movement between a retracted position for relatively high airspeed aircraft operations, and a deployed position for relatively low airspeed aircraft operations. An aerodynamic device is positionally fixed to the wing laterally adjacent the leading edge slat, the device having a forward end extending forwardly of the wing leading edge. The device is operable in response to movement of the slat into the deployed position thereof so as to improve the aerodynamics of the wing at low airspeed aircraft operations, but provides substantially no aerodynamic improvement when the slat is in the retracted position thereof during high airspeed aircraft operations.Type: GrantFiled: February 6, 2009Date of Patent: February 21, 2012Assignee: Embraer S.A.Inventor: Marcello do Areal Souto Ferrari
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Patent number: 8090485Abstract: The Tail Load Monitoring System detects faulty low frequency (e.g. those in the range from 0.1 to 1 Hz) oscillatory conditions caused by Flight Control System malfunctions while the aircraft is in air by means of a continuous assessment of the estimated tail load behavior and data processing. Both estimation and data processing activities are provided by a dedicated architecture featuring a tail load estimation module, a band-pass filter and three independent paths that continuously monitor nuisance fault detection events avoidance, catastrophic events avoidance (addressing a limit load criterion), and structural damage avoidance (addressing fatigue life criteria).Type: GrantFiled: November 27, 2007Date of Patent: January 3, 2012Assignee: Embraer S.A.Inventors: Erick Vile Grinits, Marco Antonio de Oliveira Alves Junior, Dagfinn Gangsaas, Roberto Garcia Negrao, Bianca Prazim Trotta, Fabiano Prieto Silva, Mauricio Martins de Almeida Filho, Marco Antonio Coccolin, Karina Sanches Garcia, Daniel Carmona de Campos, Cristina Minioli Saracho, Fernando Jose de Oliveira Moreira