公开(公告)号：US20200156766A1

公开(公告)日：2020-05-21

申请号：US16685243

申请日：2019-11-15

Applicant: Bombardier Inc.

Inventor： Ehud Tzabari

IPC: B64C13/50 ,  B64C13/12 ,  B64C9/02 ,  B64C13/34 ,  B64C13/14

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 plurality of independent drive devices for individually actuating the plurality of high-lift surfaces. The independent drive devices may include a power drive unit (PDU) arranged between an inboard actuator and an outboard actuator of a respective high-lift surface and an interconnecting driveline. The PDU of at least one independent drive device may include two motors having a respective motor output coupled together in a torque summing arrangement. A controller may be implemented with two independent control channels respectively coupled to one of the two motors.

公开(公告)号：US10654557B2

公开(公告)日：2020-05-19

申请号：US15513439

申请日：2015-09-24

Applicant: BOMBARDIER INC.

Inventor： Fengfeng Xi ,  Amin Moosavian ,  Allan Daniel Finistauri

IPC: B64C3/38 ,  B64C3/40 ,  B64C3/42 ,  B64C3/52 ,  B64C5/10 ,  B64C5/14 ,  B64C3/26 ,  B64C3/44 ,  B64C3/54

Abstract: A skin for an aircraft is configured to be disposed on a first rigid member and on a second rigid member. The second rigid member is movable with respect to the first rigid member and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member comprises first segments forming a first portion attached to the first rigid member and second segments forming a second portion attached to the second rigid member. The first and second portions are separated along a substantially linear seam in the absence of change in the distance and an orientation between the first rigid member and the second rigid member.

公开(公告)号：US20200148384A1

公开(公告)日：2020-05-14

申请号：US16349067

申请日：2017-11-08

Applicant: BOMBARDIER INC.

Inventor： Fidele MOUPFOUMA ,  Amadou Cisse NDOYE ,  Mohsen JALALI

IPC: B64D45/02 ,  H02G13/00

Abstract: The present disclosure provides an aircraft (10), as well as systems and methods for reducing current flow to electrical systems onboard an aircraft (10). A signal return network (220) is spaced from a composite structure (210) and first and second non-conductive components (240) are attached between the signal return network (220) and the composite structure (210) at first and second attachment points (242, 244), respectively. A conductive component (250) is attached between the signal return network (220) and the composite structure (210) at a third attachment point (246) for electrically coupling the signal return network (220) to the composite structure (210).

公开(公告)号：US10539168B2

公开(公告)日：2020-01-21

申请号：US15750928

申请日：2016-08-01

Applicant: BOMBARDIER INC.

Inventor： Rene Gallien ,  Martin Deshaies

IPC: F16M11/00 ,  F16B11/00 ,  H02G3/32 ,  F16B37/04 ,  F16M13/02 ,  F16B39/00 ,  F16L3/22

Abstract: A support assembly (10) having a structural element (12) having first and second non-parallel adjoining surfaces (18), a bracket (14) attached to the structural element (12), and a component support (16). The bracket (14) has a first flange (20) including a first attachment surface (24) adhesively bonded to the first surface (18) of the structural element (12), a second flange (20) including a second attachment surface (24) adhesively bonded to the second surface (18) of the structural element (12), and a connection portion (48) interconnecting the first and second flanges (20), the connection portion (48) extending spaced from the structural element (12) such that a gap (52) is defined therebetween. The component support (16) is engaged to the first flange (20). The connection portion (48) may have a lower resistance to rupture than that of the first and second flanges (20). A method of removably securing a component to a structural element is also discussed.

公开(公告)号：US10518885B2

公开(公告)日：2019-12-31

申请号：US15461905

申请日：2017-03-17

Applicant: BOMBARDIER INC.

Inventor： Philippe Erhel

IPC: B64D11/06 ,  G01G19/44 ,  G01G19/414 ,  G01G19/52

Abstract: A vehicle seat includes a seat pan and a backrest. The seat pan and the backrest are positionable with respect to one another such that the seat is configurable into at least one of a taxi, takeoff and landing position, a napping position, and a sleeping position. A swivel is disposed beneath and supporting the seat, permitting the seat to rotate about a pivotal axis. Base tracking is disposed beneath and supporting the seat, permitting the seat to move in a lateral and a longitudinal direction. A first control is provided to lock and unlock movement of the seat in at least one of the lateral and the longitudinal directions. A second control is provided to lock and unlock the swivel. The swivel is permitted to be unlocked while movement of the seat in the lateral and the longitudinal direction is locked.

公开(公告)号：US10509388B2

公开(公告)日：2019-12-17

申请号：US15320975

申请日：2015-05-29

Applicant: BOMBARDIER INC.

Inventor： Laurent Regnault ,  Sebastien Sirois

IPC: G05B19/402 ,  B64F5/10

Abstract: There is described a method and system for reshaping a component for assembly that may have been deformed pre-assembly and post-fabrication. As-fabricated measurements are used to determine a baseline for the component and as-mounted measurements are used to determine a deformation parameter as a function of the baseline. The component may be reshaped using correction displacements applied to a positioning device of an assembly tool to which the component is mounted for assembly.

公开(公告)号：US20190329889A1

公开(公告)日：2019-10-31

申请号：US16396274

申请日：2019-04-26

Applicant: Bombardier Inc.

Inventor： Nelson J. Afonso ,  Carolin M. Zakee

IPC: B64D11/00

Abstract: A Passenger Service Unit (PSU) including an outer plate having an aperture therethrough. The outer plate has symmetry about at least one outer plate axis. The outer plate is configured to be couplable to a passenger compartment at a first position and a second position nonadjacent to the first position. The PSU also includes a first insert configured to be coupled to the outer plate and includes at least one component to be manipulated by a passenger in the passenger compartment. The first insert has symmetry about at least one insert axis and at least a portion of the first inner plate fits within the aperture. Further, the inner plate is rotatable with respect to the outer plate such that the inner plate can be coupled to the outer plate in a first orientation and a second orientation offset by substantially 180 degrees from the first orientation.

公开(公告)号：US10459434B2

公开(公告)日：2019-10-29

申请号：US15513844

申请日：2015-09-21

Applicant: BOMBARDIER INC.

Inventor： Laurent Regnault

IPC: G05B19/418 ,  G07C3/14 ,  G01B21/04

Abstract: There is described herein an inspection tool for use during the inspection of components as manufactured. The inspection tool allows the comparison of measurement data with nominal data and provides complementary information with regards to at least one feature of the component.

公开(公告)号：US20190322356A1

公开(公告)日：2019-10-24

申请号：US16312599

申请日：2017-06-23

Applicant: BOMBARDIER INC.

Inventor： Thomas AHN ,  Grace Shwu Jen TANG ,  Farzad MOKHTARIAN ,  Gerardus Herbertus DE KOK ,  Sebastien Eric Benoit VIGNERON

IPC: B64C13/50 ,  B64C13/18

Abstract: The present disclosure provides methods and system for controlling the operation of an aircraft aileron which comprises an inboard portion and an outboard portion. A velocity of the aircraft is determined. Then, based on the velocity of the aircraft, the aileron is caused to move in certain ways. Below a first velocity threshold, the inboard aileron portion and the outboard aileron portion are caused to move substantially in unison. Between the first velocity threshold and a second, greater, velocity threshold, the outboard portion of the aileron is caused to lock and the inboard portion of the aileron is caused to move independently from the outboard portion. Above the second velocity threshold, the inboard portion is caused to move substantially opposite from the outboard portion.

公开(公告)号：US20190300192A1

公开(公告)日：2019-10-03

申请号：US16386678

申请日：2019-04-17

Applicant: BOMBARDIER INC.

Inventor： Stephen COLAVINCENZO ,  Andre BRODEUR ,  Alexis CARON L'ECUYER

IPC: B64D31/12 ,  F02C9/42 ,  F02C9/18 ,  F02C9/28

Abstract: Methods and related apparatus for improving synchronization of two or more engines on an aircraft are disclosed. Such method may be used where each engine comprises a first spool and a second spool, and, where a rotational speed of a first spool of a first engine has been substantially synchronized with a rotational speed of a first spool of a second engine. An exemplary method comprises receiving a value of a sensed parameter useful in controlling the first engine; adding a bias to the value; and using the biased value for controlling the first engine to cause a change in rotational speed of the second spool of the first engine in relation to the rotational speed of the first spool of the first engine.