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公开(公告)号：US20200307765A1
公开(公告)日：2020-10-01
申请号：US16816589
申请日：2020-03-12
申请人： EMBRAER S.A.
摘要： An aircraft wing is provided having a wing leading edge, a cut-out opening in the wing leading edge, a telescopic tube extending through the cut-out opening and connected to an internal duct of a wing leading edge slat to establish fluid communication with heated air associated with an aircraft anti-icing system, wherein the telescopic tube is moveable between retracted and extended conditions in response to the wing leading edge slat being moved between slat retraction and deployment positions, respectively, and a cover assembly comprising a cover member operatively connected to the telescopic tube to close the cut-out opening and allow synchronous movement of the cover member with the telescopic tube in response to the telescopic tube being moved between the retracted and extended conditions thereof.
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公开(公告)号：US10598201B2
公开(公告)日：2020-03-24
申请号：US15528863
申请日：2015-11-24
申请人： EMBRAER S.A.
摘要： There is described a method of mounting inserts, comprising the following steps: •(i) Application of an adhesive film on one of the faces of an inserts tray (223) covering a plurality of through-holes (241) and respective depressions (242); •(ii) Insertion of an insert (230) in each through-hole (241) of the tray (223) from a face of the inserts tray (223) opposite that of the adhesive film, securing one surface of the insert (23) onto this adhesive film; •(iii) Cutout of the adhesive film forming a plurality of single films (245) associated with the inserts (230). There is further described an insert mounting device (300), comprising a holding table (314) held by a supporting base (311), the insert mounting device (300) further comprising a rotating tray holder (312), cooperating with a cutting system (313).
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83.发明申请公开(公告)号：US20200079501A1
公开(公告)日：2020-03-12
申请号：US16564350
申请日：2019-09-09
申请人： EMBRAER S.A.
发明人： Júlio Cesar GRAVES , Yasser Mahmud ABDALLAH , Leandro Guimarães MAIA , Carlos Eduardo Vieira DE SOUZA , Luiz Felipe Ribeiro VALENTINI
IPC分类号： B64C27/57 , B64C27/26 , B64C27/30 , B64C27/68 , B64C29/00 , B64C9/00 , B64D35/02 , B64C5/02 , B64C11/00
摘要： Vertical takeoff and landing (VTOL) aircraft are provided with fixed-position port and starboard wings extending laterally from an elongate fuselage having an empennage at an aft end of the fuselage and a propeller to provide horizontal thrust to the aircraft in a direction of the longitudinal axis thereof. A series of port and starboard rotor units are provided, each of which includes axially opposed rotor blades, and a motor to rotate the rotor blades and provide vertical thrust to the aircraft. A logic control unit (LCU) controllably sets an angular position of the opposed rotor blades along a position axis relative to the longitudinal axis of the aircraft in response to determining an optimal position of the rotor blades during cruise flight operation to thereby minimize airflow disruption over the fixed-position wings.
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84.发明授权公开(公告)号：US10529248B2
公开(公告)日：2020-01-07
申请号：US14741175
申请日：2015-06-16
申请人： Embraer S.A.
摘要： A system and method for training an aircraft pilot employs a station that delivers training lessons in the form of output and also receives input data from the trainee. An apparatus comprising a computational system is capable of displaying content from different types of media, including virtual reality, augmented reality, and variations. A mixed reality environment interacts with a human being, simulating the response of real objects, and also provides necessary information to achieve Learning Objectives for a specific part of training. A register or record of the interactions is used for evaluation.
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公开(公告)号：US10453349B2
公开(公告)日：2019-10-22
申请号：US15056747
申请日：2016-02-29
申请人： Embraer S.A.
摘要： A system for warning a flight crew of potential runway overruns during landing comprises a computer processor implementing at least one neural network comprising plural inputs and at least one output. The inputs comprise at least one or more of the following: pressure altitude, air temperature, wind speed, weight, calibrated airspeed, autobrake setting, runway slope, and runway condition. The system uses the neural network to continually calculate at least the remaining distance on the runway and to generate an alert when the remaining distance is insufficient.
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公开(公告)号：US10449725B2
公开(公告)日：2019-10-22
申请号：US15378520
申请日：2016-12-14
申请人： EMBRAER S.A.
发明人： Fábio Angheben Weber , Cleber Vasquez De Mesquita , Felipe Henrique Gouvea , Paulo Alexandre De Barros Mendes
摘要： Anti-paint cracking systems are provided as part of a painted aerospace component (e.g., a fuselage, an engine nacelle, a wing, an empennage, a fairing and the like) having a pair of adjacent structural panels defining therebetween a joint space having a lengthwise extent and a finished paint topcoat covering an exterior surface of the adjacent structural panels and the joint space therebetween. The anti-paint cracking system will thus be associated with the joint space along the lengthwise extent thereof and positioned below the finished paint topcoat. The anti-paint cracking system will include a joint sealant positioned in the joint space and an adhesive tape or a fibrous tape formed of a fiber composite material applied over the joint space and the joint sealant positioned therein.
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公开(公告)号：US10414505B2
公开(公告)日：2019-09-17
申请号：US15256280
申请日：2016-09-02
申请人： Embraer S.A.
发明人： Bernardo Campos da Silva Franco , Leandro Coelho Herd , André Mendes Quintino , Nicolau Braga Santos
摘要： An environmental control system for an aircraft uses engine bleed air for cabin environment control. The environment control system regulates the inlet airflow by assessing a plurality of parameters that provides, but not limited to, the aircraft operating conditions and external environment data, aiming at substantially reducing the extracted engine bleed air demand for cabin environment control and fuel consumption reduction and concurrently complying with aircraft pressurization, ventilation and thermal load requirements. The environmental control system airflow target is calculated based on the actual aircraft operating conditions, external environment data and a multi-dimensional airflow schedule map. Then, environmental control system airflow target is further trimmed based on the actual aircraft operating conditions and air conditioning system performance capabilities by fixing the air conditioning airflow outlet temperature and then regulating the air conditioning inlet mass airflow through the flow control valve. The first control method reduces and the second one trims the environmental control system airflow target comparing to conventional control methods. Thus, fuel consumption reduction is obtained when the environment control system airflow target (extracted bleed air demand) can be reduced and or trimmed depending on flight conditions.
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88.发明申请公开(公告)号：US20190127079A1
公开(公告)日：2019-05-02
申请号：US15801485
申请日：2017-11-02
申请人： Embraer S.A.
CPC分类号： B64D43/02 , B64C13/16 , B64C13/503 , B64D15/22 , B64D45/00 , G05D1/0816
摘要： This non-limiting technology proposes to modify the maximum angle of attack setting (αsetting) of the Stall Protection or Stall Warning Systems continuously or continually, according to the elapsed time since icing is first detected and/or the deicing system was activated. A changing maximum angle of attack setting maintains approximately the same angle-of-attack margin to the stall angle-of-attack by taking into account improvements in the stall angle of attack due to inflight icing removal and icing prevention by operation of an inflight deicing system. The aircraft flying with an angle of attack closer to the critical angle of attack is capable of producing a higher coefficient of lift.
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公开(公告)号：US10222301B2
公开(公告)日：2019-03-05
申请号：US15146711
申请日：2016-05-04
申请人： Embraer S.A.
发明人： Paulo Anchieta Da Silva , Marcelo Rosa Suzuki , Ricardo Rogulski , Andre Koji Fujimoto Tamba , Luís Gustavo Dos Santos
IPC分类号： G01M13/00 , G06F3/0481 , G01M99/00 , G06K7/10
摘要： An inspection system for assessing and visualizing structural damage to a structural platform comprises sensors operatively coupled to the structural platform that assess structural damage to or failure of the structural platform. A structural health monitoring processor operatively coupled to the sensors determines structural damage in response to the sensors. At least one RF transponder and associated reader determines the position of the structural platform relative to a user augmented reality viewing device. The user augmented reality viewing device includes a camera that captures images of the structural platform. The user augmented reality viewing device displays real world images of the structural platform and virtual indications of determined structural damage that are dependent on the position and orientation of the user augmented reality viewing device relative to the structural platform.
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90.发明授权公开(公告)号：US10112701B2
公开(公告)日：2018-10-30
申请号：US14851182
申请日：2015-09-11
申请人： EMBRAER S.A.
发明人： Carlos Rogulski Filho , David Dias Ferraz , Graco Tognozzi Lopes , Arilton Nunes De Mattos , Claudio De Martino
摘要： Landing gear doors may be opened in an emergency event, e.g., a failure of the normal landing gear actuation system that requires a gravity free-fall deployment. The retractable aircraft landing gear door actuation mechanism will include a landing gear door and a door support bracket attached to the landing gear door. The support bracket is attached to aircraft structure for pivotal movement about a pivot axis between a closed condition whereby the landing gear door covers an aircraft landing gear when retracted relative to the aircraft structure, and an opened condition whereby the landing gear door is moved laterally and upwardly relative to the aircraft landing gear when extended relative to the aircraft structure. A gear door actuation assembly is operatively connected to the door support bracket for moving the door support bracket and the gear door supported thereby between the closed and opened conditions thereof. The gear door actuation assembly will include an over-the-center spring assembly which assists in pivotal movement of the door support bracket and the gear door supported thereby from the closed condition into the opened condition thereof.
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