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71. 发明授权

EP3478576B1 SPLIT-AILERON CONTROL 有权
公开(公告)号：EP3478576B1
公开(公告)日：2020-08-05
申请号：EP17742546.9
申请日：2017-06-23
申请人： Bombardier Inc. , Short Brothers Plc
发明人： AHN, Thomas , TANG, Grace Shwu Jen , MOKHTARIAN, Farzad , DE KOK, Gerardus Herbertus , VIGNERON, Sébastien Eric Benoit
IPC分类号： B64C13/50

72. 发明授权

EP2855275B1 LIGHTING ARRAY FOR AN AIRCRAFT 有权
公开(公告)号：EP2855275B1
公开(公告)日：2020-07-29
申请号：EP13728899.9
申请日：2013-05-30
申请人： Bombardier Inc. , Learjet Inc.
发明人： GAGNON, Pierre , LETENDRE, Nicolas
IPC分类号： B64D47/04 , B64D47/06 , B64D47/02

73. 发明授权

EP3538440B1 SIGNAL RETURN NETWORK FOR COMPOSITE AIRCRAFT 有权
公开(公告)号：EP3538440B1
公开(公告)日：2020-07-15
申请号：EP17809017.1
申请日：2017-11-08
申请人： Bombardier Inc. , Short Brothers Plc
发明人： MOUPFOUMA, Fidele , NDOYE, Amadou Cisse , JALALI, Mohsen
IPC分类号： B64D45/02

74. 发明公开

EP3659926A1 COCKPIT PEDESTAL AND AIRCRAFT WITH A COCKPIT PEDESTAL 审中-公开
公开(公告)号：EP3659926A1
公开(公告)日：2020-06-03
申请号：EP19209922.4
申请日：2019-11-19
申请人： Bombardier Inc.
发明人： HARTNER, Angela , CHIRIAC, Horatiu Daniel , ELSHARKAWI, Mohamed Hassan
IPC分类号： B64D43/00
摘要： A cockpit pedestal (100) and an aircraft with a cockpit pedestal. The cockpit pedestal (100) includes an integrally-formed frame (110) including an instrument receiving portion (114) defining a plurality of compartments (120) for receiving instruments (80) therein; and a plurality of legs (140) supporting the instrument receiving portion (114), the plurality of legs (140) being integrally formed with the instrument receiving portion (114), the plurality of legs being adapted for transferring a load of the plurality of instruments from the instrument receiving portion to a floor of the aircraft cockpit (20) when the cockpit pedestal and the instruments are installed in the aircraft cockpit. In some versions the cockpit pedestal includes a conductive layer (150) electrically grounding the instruments in the cockpit.

75. 发明公开

EP3628584A1 AIRCRAFT DOOR AND METHOD OF OPERATING THE SAME 审中-公开
公开(公告)号：EP3628584A1
公开(公告)日：2020-04-01
申请号：EP19196153.1
申请日：2019-09-09
申请人： Bombardier Inc.
发明人： ST-JEAN, Frederic , BEAUCHAMP, Charles , MITWALY, Mohamed
IPC分类号： B64C1/14
摘要： There is disclosed an emergency door positionable in an exit opening of an aircraft. The door has door supports mountable to the lower wall and each having a pivot point. A first pivot axis is defined between the pivot points. A block is mountable to the lower wall and is offset from a center of the lower wall. A door body is mountable within the opening to the door supporting structure and pivotally mountable to the door supports. The door body is pivotable about the first pivot axis from an initial position in which the door body is within the opening, until the door body is disengaged from the door supports. A bottom portion of the door body abuts against the block to define a removal pivot point. The door body is pivotable about the removal pivot point to remove the door body from the exit opening.

76. 发明公开

EP3619108A1 AIRCRAFT WING-TO-FUSELAGE INTERFACE PERMITTING POSITIONAL ADJUSTMENT 有权
公开(公告)号：EP3619108A1
公开(公告)日：2020-03-11
申请号：EP18724334.0
申请日：2018-04-26
申请人： Bombardier Inc. , Short Brothers Plc
发明人： MURPHY, Michael , ARAUJO, Jack , SHUM, Gary , BRADLEY, George
IPC分类号： B64C1/26 , B64F5/10

77. 发明授权

EP3049601B1 ADJUSTMENT DEVICE 有权
公开(公告)号：EP3049601B1
公开(公告)日：2020-01-22
申请号：EP14790730.7
申请日：2014-09-25
申请人： Bombardier Inc. , Short Brothers Plc
发明人： MAHAITS, Martin , TREMBLAY, Michel
IPC分类号： E05D7/00 , E05D7/04 , B64D11/06

78. 发明公开

EP3584660A1 AIRCRAFT SIDESTICK PRIORITY AND DUAL INPUT CONTROL LOGIC 审中-公开
公开(公告)号：EP3584660A1
公开(公告)日：2019-12-25
申请号：EP19191987.7
申请日：2014-06-09
申请人： Bombardier Inc. , Short Brothers Plc , C SERIES AIRCRAFT LIMITED PARTNERSHIP
发明人： OUELLETTE, Benoit , DUCHESNE, Sophie , LECOQ, Frederic
IPC分类号： G05D1/00 , B64C13/04
摘要： A flight control system for an aircraft comprises a processor that processes a plurality of inputs from the aircraft, that contains a plurality of control laws that control operation of the aircraft, and that provides a plurality of outputs that control a plurality of devices located on the aircraft. Also included is a pair of first input devices, wherein a first one of the first input devices is controlled by a pilot of the aircraft, a second one of the first input devices is controlled by a co-pilot of the aircraft, each one of the first input devices being operable to input a first control signal to the processor to cause the aircraft to be in a momentary first priority control condition; and a pair of second input devices located apart from the pair of first input devices, a first one of the second input devices controlled by a pilot of the aircraft, a second one of the second input devices controlled by a co-pilot of the aircraft, each one of the second input devices being operable to input a second control signal to the processor to cause the aircraft to be in a permanent second priority control condition.

79. 发明公开

EP3584154A1 AIRCRAFT WING WITH DEPLOYABLE FLAP 有权
公开(公告)号：EP3584154A1
公开(公告)日：2019-12-25
申请号：EP19180621.5
申请日：2019-06-17
申请人： Bombardier Inc.
发明人： ILIESCU, Vlad
IPC分类号： B64C9/02 , B64C9/16
摘要： An aircraft wing (5) includes a groove (20) extending along a length between a forward extremity (22A) and an aft extremity (22B). A forward segment (24A) of the groove (20) extends upwardly to the forward extremity (22A). The forward extremity (22A) is a highest point of the groove. A flap carriage (32) is mounted to the groove (20) and displaceable therealong. A flap (10) is pivotably attached to the flap carriage (32) to define a flap pivot axis (35A) about which the flap (10) is rotatable. The flap (10) is displaceable with the flap carriage (32). An actuator (40) has an arm (44) being extendable between an extended position and a retracted position to displace the flap carriage (32) along the groove (20). The flap carriage (32) in the retracted position being disposed in the forward segment (24A) of the groove (20) and the flap (10) being rotated about the flap pivot axis (35A) to position the flap trailing edge (11B) in negative flap deployment.

80. 发明公开

EP3584153A1 VARIABLE CAMBER SYSTEM 审中-公开
公开(公告)号：EP3584153A1
公开(公告)日：2019-12-25
申请号：EP19181074.6
申请日：2019-06-18
申请人： Bombardier Inc.
发明人： MOKHTARIAN, Farzad
IPC分类号： B64C3/50 , B64C9/18 , B64C9/08 , B64C9/02 , B64C9/06
摘要： A flap and spoiler system (300) of an aircraft wing including a spoiler (304) having a spoiler leading edge and a spoiler trailing edge (310). The flap and spoiler system (300) also includes a flap (306) having a flap leading edge (314) and a flap trailing edge (312), an axis of rotation (322) through the flap, and a top surface portion (332) above the axis of rotation (322). The top surface portion (332) has a first semi-circular shape (334) such that, when the flap (306) rotates about the axis of rotation (322), the spoiler trailing edge (310) remains substantially stationary. When the spoiler trailing edge (310) remains substantially stationary the spoiler is not driven by a spoiler drive.

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