公开(公告)号：WO2013052784A1

公开(公告)日：2013-04-11

申请号：PCT/US2012/058929

申请日：2012-10-05

Applicant: BOMBARDIER INC. ,  LEARJET INC. ,  SAVARD, David ,  BARDIER, Rene ,  LAROSE, Martin ,  GILLES, Michael ,  TREMBLAY, Michel ,  OLESON, Michael ,  SUAREZ, Alfredo

Inventor： SAVARD, David ,  BARDIER, Rene ,  LAROSE, Martin ,  GILLES, Michael ,  TREMBLAY, Michel ,  OLESON, Michael ,  SUAREZ, Alfredo

IPC: B64D11/06

CPC classification number: B64D11/06 ,  B64D11/00 ,  B64D11/0641 ,  B64D2011/0069 ,  B64D2011/0076 ,  Y02T50/46

Abstract: A divan (10) includes a seating surface (32) and a backrest (34). In a first configuration, the backrest (34) is positioned adjacent to the seating surface (32) to support a person's back while the person is seated on the seating surface (32). In the first configuration, the seating surface (32) is disposed at a first predetermined height above a horizontal plane. In a second configuration, the backrest (34) establishes an upper bunk (94) above the seating surface. In the second configuration, the seating surface (32) establishes a lower bunk (92) beneath the upper bunk (94). In the second configuration, the seating surface (32) is disposed at a second predetermined height that is lower than the first predetermined height.

Abstract translation: 沙发（10）包括座位表面（32）和靠背（34）。 在第一配置中，靠背（34）邻近座位表面（32）定位，以在人坐在就座表面（32）上时支撑人的背部。 在第一构造中，座面（32）设置在水平面上方的第一预定高度。 在第二配置中，靠背（34）在就座表面上方建立一个上层（94）。 在第二构造中，就座表面（32）在上铺板（94）的下面建立一个下层铺（92）。 在第二构造中，座表面（32）设置在低于第一预定高度的第二预定高度处。

公开(公告)号：WO2018005534A1

公开(公告)日：2018-01-04

申请号：PCT/US2017/039557

申请日：2017-06-27

Applicant: BOMBARDIER INC. ,  LEARJET INC.

Inventor： BUDNITSKY, Dmitry ,  SMITH, Howard, Ian ,  HANSON, Thomas

IPC: B64C9/16 ,  B64C9/02

Abstract: Trailing edge assemblies, couplers and methods for deploying a trailing edge flap of an aircraft wing are disclosed. An exemplary method disclosed herein comprises guiding an aft portion of the trailing edge flap (28) along an elongated track member (36C) as the trailing edge flap (28) moves toward the deployed position; guiding a forward portion of the trailing edge flap (28) along the elongated track member (36C) as the trailing edge flap (28) moves toward the deployed position; and accommodating transverse movement of the forward portion of the trailing edge flap (28) relative to the elongated track member (36C).

Abstract translation: 公开了用于展开飞机机翼的后缘襟翼的后缘组件，联接件和方法。 本文公开的示例性方法包括随着后缘襟翼（28）朝向展开位置移动而沿着细长轨道构件（36C）引导后缘襟翼（28）的后部; 随着后缘襟翼（28）向展开位置移动，沿着细长轨道构件（36C）引导后缘襟翼（28）的前部; 并适应后缘襟翼（28）的前部相对于细长轨道构件（36C）的横向运动。

公开(公告)号：WO2017218332A1

公开(公告)日：2017-12-21

申请号：PCT/US2017/036735

申请日：2017-06-09

Applicant: BOMBARDIER INC. ,  LEARJET INC.

Inventor： TIMBRELL, Dean Martin ,  GAUDREAU, Jean-Guy

IPC: B64C7/00 ,  F24F13/08 ,  E06B7/08 ,  B64D45/00 ,  A62C2/06

CPC classification number: F24F13/084 ,  A62C3/08 ,  A62C4/00 ,  B64C7/00 ,  B64D2045/009 ,  F24F11/33 ,  F24F13/082

Abstract: A ventilation louver (10) includes a first plate (52) defining a first opening (74) therein for permitting fluid flow along a first direction (128), a second plate (54) defining a vane (82) therein, the vane at least partially covering the first opening and directing the fluid flow along a second direction (130), non-parallel to the first direction, and a third plate (56) defining a louvered opening (108) therein wherein the louvered opening directs fluid flow along a third direction (138), non-parallel to both the first direction and the second direction. In a non-limiting example, the ventilation louver may be disposed in a belly fairing of an aircraft.

Abstract translation: 一种通风百叶窗（10），包括：第一板（52），其中限定第一开口（74）以允许流体沿第一方向（128）流动;第二板（54），其限定叶片 （82），所述叶片至少部分地覆盖所述第一开口并且引导所述流体流沿不平行于所述第一方向的第二方向（130）以及其中限定其中的百叶窗式开口（108）的第三板（56） 其中所述百叶窗式开口沿着不平行于所述第一方向和所述第二方向的第三方向（138）引导流体流动。 在一个非限制性示例中，通风百叶可以布置在飞机的腹部整流罩中。

公开(公告)号：WO2016049343A8

公开(公告)日：2017-06-29

申请号：PCT/US2015051996

申请日：2015-09-24

Applicant: BOMBARDIER INC ,  LEARJET INC ,  ERHEL PHILIPPE

Inventor： ERHEL PHILIPPE

IPC: B64D11/06

CPC classification number: B64D11/0648 ,  B64D11/0639 ,  B64D11/064 ,  Y02T50/46

Abstract: A seat (214) for an aircraft is provided that includes a seat pan (228), having a seat pan front edge and a seat pan rear edge, a backrest (218), having a backrest top edge and a backrest bottom edge, where the backrest bottom edge is articulately disposed adjacent to the seat pan rear edge, a headrest (216), having a headrest top edge and a headrest bottom edge, where the headrest bottom edge is articulately disposed adjacent to the backrest top edge, a tracking device (234) disposed beneath the seat pan and being attachable to a floor of the aircraft, the tracking device permitting the seat pan to translate in at least one of a lateral direction and a longitudinal direction, and a swivel (232) connected between the tracking device and the seat pan, permitting the seat pan to rotate with respect to the tracking device.

Abstract translation: 提供了用于飞机的座椅（214），其包括具有座椅底板前边缘和座椅底板后边缘的座板（228），具有靠背顶部边缘和靠背底部边缘的靠背（218），其中 靠背底部边缘铰接地设置在座椅靠背后边缘附近;头枕（216），具有头枕顶部边缘和头枕底部边缘，其中头枕底部边缘铰接地设置在靠背顶部边缘附近;跟踪装置 （234），其设置在所述座板下方并且可附接到所述飞机的地板，所述跟踪设备允许所述座板在侧向方向和纵向方向中的至少一个方向上平移;以及旋转件（232），其连接在所述跟踪件 装置和座板，允许座板相对于跟踪装置旋转。

公开(公告)号：WO2016049343A1

公开(公告)日：2016-03-31

申请号：PCT/US2015/051996

申请日：2015-09-24

Applicant: BOMBARDIER INC. ,  LEARJET INC. ,  ERHEL, Philippe

Inventor： ERHEL, Philippe

IPC: B64D11/06

CPC classification number: B64D11/0648 ,  B64D11/0639 ,  B64D11/064 ,  Y02T50/46

Abstract: A seat (214) for an aircraft is provided that includes a seat pan (228), having a seat pan front edge and a seat pan rear edge, a backrest (218), having a backrest top edge and a backrest bottom edge, where the backrest bottom edge is articulately disposed adjacent to the seat pan rear edge, a headrest (216), having a headrest top edge and a headrest bottom edge, where the headrest bottom edge is articulately disposed adjacent to the backrest top edge, a tracking device (234) disposed beneath the seat pan and being attachable to a floor of the aircraft, the tracking device permitting the seat pan to translate in at least one of a lateral direction and a longitudinal direction, and a swivel (232) connected between the tracking device and the seat pan, permitting the seat pan to rotate with respect to the tracking device.

Abstract translation: 提供了一种用于飞行器的座椅（214），其包括具有座椅前缘和座椅后缘的座椅底座（228），具有靠背顶部边缘和靠背底部边缘的靠背（218），其中 所述靠背底部边缘邻近所述座椅后边缘铰接地设置，具有头枕顶部边缘和头枕底部边缘的头枕（216），其中所述头枕底部边缘邻近所述靠背顶部边缘被铰接地设置，跟踪装置 （234），其设置在所述座盘下方并且可附接到所述飞机的地板，所述跟踪装置允许所述座盘在横向方向和纵向方向中的至少一个上平移，以及连接在所述跟踪 装置和座盘，允许座盘相对于跟踪装置旋转。

公开(公告)号：WO2015053838A1

公开(公告)日：2015-04-16

申请号：PCT/US2014/047374

申请日：2014-07-21

Applicant: LEARJET INC. ,  CHANDRASEKHARAN, Reuben ,  IAROCCI, Nick ,  VAFA, Shermineh ,  AKEL, Iyad

Inventor： CHANDRASEKHARAN, Reuben ,  IAROCCI, Nick ,  VAFA, Shermineh ,  AKEL, Iyad

IPC: B64C5/02

CPC classification number: B64C5/02 ,  B64C9/00

Abstract: Tailplanes (24) and empennages (16) for aircraft (10) are disclosed. An exemplary tailplane (24) disclosed includes a stabilizer (30) having a fixed shape and an elevator (32) movably secured to the stabilizer (30). The elevator (32) is movable from a neutral position relative to the stabilizer (30). The stabilizer (32) and the elevator (32) define an airfoil cross-sectional shape (38) having a positive camber when the elevator (32) is in the neutral position. The positive camber of the airfoil cross-sectional shape (38) may facilitate movement of the elevator (32) during some flight conditions. Also disclosed are tailplanes (24) having camber distributions that vary along the spans of the tailplanes (24).

Abstract translation: 披露飞机（10）的飞机（24）和尾翼（16）。 所公开的示例性尾翼（24）包括具有固定形状的稳定器（30）和可移动地固定到稳定器（30）上的升降机（32）。 电梯（32）能够相对于稳定器（30）从中立位置移动。 当电梯（32）处于中立位置时，稳定器（32）和电梯（32）限定具有正弯度的翼型横截面形状（38）。 机翼横截面形状（38）的正弧度可以促进电梯（32）在某些飞行条件下的运动。 还公开了具有沿着尾板（24）的跨度变化的弯度分布的尾板（24）。

公开(公告)号：WO2014201225A1

公开(公告)日：2014-12-18

申请号：PCT/US2014/042080

申请日：2014-06-12

Applicant: BOMBARDIER INC. ,  LEARJET INC. ,  BOUCHER, Frederic ,  RIBAS, Clovis S.

Inventor： BOUCHER, Frederic ,  RIBAS, Clovis S.

IPC: B64C25/22 ,  B64C25/26 ,  F15B15/00

CPC classification number: B64C25/22 ,  B64C25/26

Abstract: A landing gear system includes landing gear (22), an uplock (26) that is releasably engageable with the landing gear (22), an uplock hydraulic actuator (16) operably connected to the uplock (26), a landing gear hydraulic actuator (14) operatively connected to the landing gear, and a controller (C) operatively connected to the uplock hydraulic actuator (16) and the landing gear hydraulic actuator. In response to receipt of a command to deploy the landing gear, the controller (C) actuates the uplock hydraulic actuator (16) and the landing gear hydraulic actuator (14) to the UP condition and then actuates the uplock hydraulic actuator (16) and the landing gear actuator (14) to the DOWN condition. An alternative embodiment incorporates a piloted check valve (42) upstream of the landing gear hydraulic actuator. The piloted check valve (42) delays operation of the landing gear hydraulic actuator (14) until release of the landing gear (22) by the uplock (26).

Abstract translation: 起落架系统包括起落架（22），可与起落架（22）可释放地接合的上下摆（26），可操作地连接到起重装置（26）的升降液压致动器（16），起落架液压致动器 操作地连接到起落架的控制器（C）和可操作地连接到上锁液压致动器（16）和起落架液压致动器的控制器（C）。 响应于接收到部署起落架的命令，控制器（C）将升压液压致动器（16）和起落架液压致动器（14）致动到UP状态，然后致动上锁液压致动器（16）和 起落架致动器（14）处于DOWN状态。 替代实施例包括起落架液压致动器上游的导向止回阀（42）。 引导式止回阀（42）延迟起落架液压致动器（14）的操作，直到起落架（22）通过上锁（26）释放。

公开(公告)号：WO2013192483A1

公开(公告)日：2013-12-27

申请号：PCT/US2013/046952

申请日：2013-06-21

Applicant: BOMBARDIER INC. ,  LEARJET INC. ,  XI, Fengfeng ,  FINISTAURI, Allan, Daniel ,  MOOSAVIAN, Amin

Inventor： XI, Fengfeng ,  FINISTAURI, Allan, Daniel ,  MOOSAVIAN, Amin

IPC: B64C3/44 ,  B64C3/52

CPC classification number: B64C3/38 ,  B64C3/385 ,  B64C3/40 ,  B64C3/44 ,  B64C3/52 ,  B64C3/54 ,  B64C2003/445 ,  B64C2003/543 ,  Y02T50/14

Abstract: A morphing wing for an aircraft includes a top surface, a bottom surface, a leading edge, a trailing edge, a tip, and a root. A plurality of structural ribs (76,78) is disposed between the root and tip so that they extend between the top surface and the bottom surface and intersect with a lateral axis thereof. At least one active member (88,90,92,94) connects between two adjacent structural ribs along or at a first angle to the lateral axis. The active member is actively adjustable. At least one passive member (80,82,84,86) connects between the two adjacent structural ribs along or at a second angle to the lateral axis. The passive member is passively adjustable. Adjustment of at least one active member moves the adjacent structural ribs with respect to one another, thereby morphing the wing from a first configuration to a second configuration.

Abstract translation: 用于飞机的变形翼包括顶表面，底表面，前缘，后缘，尖端和根部。 多个结构肋（76,78）设置在根部和尖端之间，使得它们在顶表面和底表面之间延伸并与其横向轴线相交。 至少一个有效构件（88,90,92,94）沿着或相对于横向轴线以第一角度连接在两个相邻的结构肋之间。 活动构件可以主动调节。 至少一个被动构件（80,82,84,86）沿着或相对于横向轴线的第二角度在两个相邻的结构肋之间连接。 被动构件被动调节。 至少一个活动构件的调节使相邻的结构肋相对于彼此移动，从而使机翼从第一构型变形到第二构型。

公开(公告)号：WO2012155020A2

公开(公告)日：2012-11-15

申请号：PCT/US2012/037456

申请日：2012-05-11

Applicant: BOMBARDIER INC. ,  LEARJET INC. ,  GRANT, Robert ,  BLOCK, Michael

Inventor： GRANT, Robert ,  BLOCK, Michael

IPC: E05C3/12

CPC classification number: E05C1/145 ,  B64D11/04 ,  E05B5/00 ,  E05B41/00 ,  E05B59/00 ,  E05B63/14 ,  E05B65/1086 ,  E05C1/004 ,  E05C1/04 ,  E05C1/065 ,  Y10T292/0967

Abstract: A latch includes a first locking bolt, where a first extended position of the first locking bolt defines a first locked condition and a first retracted position defines a first unlocked condition. The latch also includes a second locking bolt, where a second extended position of the second locking bolt defines a second locked condition and a second retracted position defines a second unlocked condition. A biasing member operatively connects to the first locking bolt to bias the first locking bolt in the first extended position. A lever pivotally connects to the housing and operatively connects to the first locking bolt such that movement of the lever from a closed position to an opened position causes at least the first locking bolt to move from the first extended position to the first retracted position. A locking indicator is provided in associated with the second locking bolt.

Abstract translation: 闩锁包括第一锁定螺栓，其中第一锁定螺栓的第一延伸位置限定第一锁定状态，并且第一缩回位置限定第一解锁状态。 闩锁还包括第二锁定螺栓，其中第二锁定螺栓的第二延伸位置限定第二锁定状态，而第二缩回位置限定第二解锁状态。 偏置构件可操作地连接到第一锁定螺栓，以将第一锁定螺栓偏压在第一延伸位置。 杠杆枢转地连接到壳体并且可操作地连接到第一锁定螺栓，使得杠杆从关闭位置到打开位置的运动使得至少第一锁定螺栓从第一延伸位置移动到第一缩回位置。 锁定指示器设置成与第二锁定螺栓相关联。

公开(公告)号：WO2018067370A1

公开(公告)日：2018-04-12

申请号：PCT/US2017/053947

申请日：2017-09-28

Applicant: BOMBARDIER INC. ,  LEARJET INC.

Inventor： CARON-L'ECUYER, Alexis ,  BRODEUR, Andre

IPC: B64D13/06 ,  F24F13/24 ,  F24F13/068

Abstract: An air duct includes a first chamber and a second chamber, the first chamber being defined between an air handling device and the second chamber, and the second chamber being defined between the first chamber and an environment exterior to the air duct, a plurality of first openings between the first chamber and the second chamber, a plurality of second openings between the second chamber and the environment exterior to the air duct, and a sound absorbing material defining at least a portion of an interior surface of at least one of the first chamber and the second chamber.

Abstract translation: 空气管道包括第一腔室和第二腔室，第一腔室限定在空气处理装置与第二腔室之间，并且第二腔室限定在第一腔室与第一腔室外部的环境之间 所述空气管道，所述第一腔室与所述第二腔室之间的多个第一开口，所述第二腔室与所述空气管道外部的环境之间的多个第二开口以及限定至少一部分内表面 的第一腔室和第二腔室中的至少一个。