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21.发明授权公开(公告)号：US11338927B2
公开(公告)日：2022-05-24
申请号：US16708711
申请日：2019-12-10
Applicant: BOMBARDIER INC.
Inventor： Martin Abramian
Abstract: An aircraft including a fuselage extending along a longitudinal axis; forward swept wings extending from the fuselage; at least one horizontal stabilizer secured to the fuselage; and a distributed electrical propulsion system operatively connected to an electrical power source. The distributed electrical propulsion system have an air intake located rearward of an intersection between the forward swept wings and the fuselage open to a boundary layer region on a surface of the fuselage.
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公开(公告)号：US11300001B2
公开(公告)日：2022-04-12
申请号：US16431819
申请日：2019-06-05
Applicant: BOMBARDIER INC.
Inventor： Claude J. P. Lavoie , Jean-Hugues Li
Abstract: Systems and methods associated with electrical systems of aircraft are disclosed. A method disclosed herein comprises generating electricity using an electric generator operatively coupled to an engine of the aircraft, supplying the electricity generated using the electric generator to a baseline power bus; generating electricity using an electric starter generator operatively coupled to the engine; and supplying the electricity generated using the electric starter generator to a supplemental power bus independent from the baseline power bus.
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公开(公告)号：US11266252B2
公开(公告)日：2022-03-08
申请号：US16464987
申请日：2017-11-07
Applicant: BOMBARDIER INC.
Inventor： Michel Tremblay , Gradyn Ladd
Abstract: A storage container (100) has a base (102) defining at least one storage compartment (202, 204, 206, 208, 210, 212), a top (104) movable between closed and opened positions, latching and locking assemblies. The latching assembly (500) has a latching actuator (110) movable between first and second positions. The latching assembly (500) locks the top (104) to the base (102) when the top (104) is in the closed position and the latching actuator (110) is in the first position and releases the top (104) from the base (102) when the latching actuator (110) is in the second position. The locking assembly has a lock actuator (801) having actuated and released positions. The top (104) is movable when the lock actuator (801) is in the actuated position. The locking assembly locking the top (104) in the open, closed, or an intermediate position when the lock actuator (801) is in the released position. The latching actuator (110) and the lock actuator (801) are operatively connected to the top (104) and move with the top (104) between the closed and the opened position.
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公开(公告)号：US11242131B2
公开(公告)日：2022-02-08
申请号：US16685391
申请日：2019-11-15
Applicant: Bombardier Inc.
Inventor： Ehud Tzabari
Abstract: A high-lift actuation system for differentially actuating a plurality of high-lift surfaces of an aircraft is disclosed. An exemplary high-lift actuation system includes a centralized drive device for centralized actuation control of an inboard high-lift surface of a first wing and a second wing, respectively, and at least two independent drive devices for individual actuation control of an outboard high-lift surface of the first wing and the second wing, respectively. The centralized drive device may include a central power drive unit (PDU) operably coupled to a common central driveline for driving the inboard high-lift surfaces, and the common central driveline may be separate and spaced apart from a respective driveline of the independent drive devices. The common central driveline may mechanically synchronize movement of the inboard high-lift surfaces, and a controller may electronically coordinate synchronized movement and controlled differential movement of the plurality of high-lift surfaces.
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25.发明授权公开(公告)号：US11225320B2
公开(公告)日：2022-01-18
申请号：US16661411
申请日：2019-10-23
Applicant: BOMBARDIER INC.
Inventor： Sylvain Therien , David Reist
Abstract: Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.
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Patent Agency Ranking
公开(公告)号：US11186353B2
公开(公告)日：2021-11-30
申请号：US16696099
申请日：2019-11-26
Applicant: BOMBARDIER INC.
Inventor： John Richard Savidge
Abstract: A mobile platform with a passenger door system having stairs with one or more deployable lower steps and associated methods for deployment and/or stowing of such lower steps are disclosed. In one embodiment, the method comprises using movement of the door to drive a movement of a handrail associated with the stairs, and using the movement of the handrail to drive a movement of the one or more lower steps.
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27.发明申请公开(公告)号：US20210341946A1
公开(公告)日：2021-11-04
申请号：US17038441
申请日：2020-09-30
Applicant: BOMBARDIER INC.
Inventor： Aymeric KRON
Abstract: Methods and systems for controlling a bank angle, a heading angle and an altitude of an aircraft during flight are provided. The methods and systems disclosed herein make use of sliding mode control and feedback linearization control (nonlinear dynamic control) techniques. The methods and systems can provide autopilot-type functions that can autonomously execute aggressive maneuvers as well as more gentle maneuvers for aircraft.
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公开(公告)号：US20210254556A1
公开(公告)日：2021-08-19
申请号：US17174537
申请日：2021-02-12
Applicant: BOMBARDIER INC.
Inventor： Mario ASSELIN
Abstract: Systems and methods for varying excess thrust of an aircraft include: a first electric fan rotatable about a first axis for directing a first air flow along a first air flow path; and a second electric fan rotatable about a second axis different from the first axis for directing a second air flow along a second air flow path fluidly isolated from the first air flow path, wherein the first electric fan and the second electric fan are disposed radially about a roll axis of the aircraft and adjacent an aft end of the aircraft, and the first electric fan and the second electric fan are configured to intake boundary layer air to form the first air flow and the second air flow.
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公开(公告)号：US11040776B2
公开(公告)日：2021-06-22
申请号：US16556523
申请日：2019-08-30
Applicant: BOMBARDIER INC.
Inventor： Philippe Andre Eugene Erhel
Abstract: An aircraft divan includes a lateral bracket connecting between front and rear legs with lateral bracket front and rear ends, a first track defined by the lateral bracket between the lateral bracket front and rear ends, an upright, having upright top and bottom ends, a second track defined by the upright between the upright top and bottom ends, a seat pan having seat pan front and rear ends, the seat pan being slidingly connected to the first track adjacent to the seat pan rear end, and a backrest having backrest top and bottom ends, the backrest being slidingly connected to the second track adjacent to the backrest top end. The seat pan rear end is pivotably connected to the backrest adjacent to the backrest bottom end such that movement of the seat pan is transmitted to the backrest so as to move together between upright and berth positions.
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公开(公告)号：US20210179272A1
公开(公告)日：2021-06-17
申请号：US17167298
申请日：2021-02-04
Applicant: BOMBARDIER INC.
Inventor： Seung Joon BANG , Louis GAGNON-SEGUIN , Philippe ERHEL , Tim FAGAN , Alexandre CURTHELET , Vincent DUMAIS , René BARDIER , Paul FROMONT , Gradyn LADD , Jean-Philippe GUIMOND , Mario BRUNET
IPC: B64D11/06
Abstract: An aircraft cabin comprising a credenza and a lounge chair disposed above the credenza is disclosed. The lounge chair is adjustable between a first configuration defining a first seating arrangement and a second configuration defining a second seating arrangement. Also disclosed is a mechanism to facilitate the adjustment of the lounge chair.
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