公开(公告)号：US09663225B1

公开(公告)日：2017-05-30

申请号：US15417113

申请日：2017-01-26

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  George Ryan Decker ,  Andrew G. Baines ,  David R. Bockmiller ,  Erick Wayne Kohler

IPC: B64C29/00 ,  B64F5/40

CPC classification number: B64C29/0033 ,  B64C27/22 ,  B64D35/00 ,  B64F5/40 ,  F16H1/006 ,  Y10T29/49318 ,  Y10T74/1966

Abstract: A drive system for a tiltrotor aircraft includes a first gearbox rotatably mounted to the airframe and rotatable about a longitudinal axis to operate the tiltrotor aircraft between helicopter and airplane modes. A second gearbox extends generally normal to the longitudinal axis of the first gearbox. A common shaft, rotatable about the longitudinal axis, transfers torque from an output gear of the second gearbox to an input gear of the first gearbox. A support assembly couples the second gearbox to the airframe and includes a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox that is not parallel with the first radial growth degree of freedom.

公开(公告)号：US20170144746A1

公开(公告)日：2017-05-25

申请号：US15428687

申请日：2017-02-09

Applicant: Bell Helicopter Textron Inc.

Inventor： Troy Cyril Schank ,  Carlos Alexander Fenny ,  Andrew Maresh ,  Chyau-Song Tzeng

IPC: B64C11/28 ,  B64C27/30 ,  B64C11/32 ,  B64C29/00

CPC classification number: B64C11/28 ,  B64C27/30 ,  B64C29/0033 ,  B64D27/20

Abstract: A mechanism for transitioning a tiltrotor aircraft between rotary and non rotary flight modes. The mechanism includes a gimbal lock positioned about a mast that is operable to selectively enable and disable a gimballing degree of freedom of a rotor assembly relative to the mast. A blade stop assembly, positioned about the mast, includes a plurality of arms having a radially contracted orientation and a radially extended orientation. A blade lock assembly is operably associated with each rotor blade assembly. Each blade lock assembly is operable to selectively enable and disable a folding degree of freedom and a pitching degree of freedom of the respective rotor blade assembly. A swash plate is operable to change the pitch of the rotor blade assemblies in the rotary flight mode and fold the rotor blade assemblies in the non rotary flight mode.

公开(公告)号：US09653842B2

公开(公告)日：2017-05-16

申请号：US14703296

申请日：2015-05-04

Applicant: Textron, Inc.

Inventor： Zachary Ronald Savage ,  John Ledden ,  Arthur James Harvey ,  John Frederick Criss, Jr.

IPC: H01R13/52 ,  H01R12/70 ,  H01R13/447

CPC classification number: H01R13/5227 ,  H01R12/7076 ,  H01R13/447 ,  H01R13/5213

Abstract: The present disclosure provides a USB connection system for an open cab vehicle such as a golf car, turf-care vehicle, small maintenance vehicle, shuttle vehicle, cargo vehicle, all-terrain vehicle, utility terrain vehicle, motorcycle, and/or other utility vehicle, and/or other outdoor/off-road vehicle. The USB connection system comprises a module structured and operable to receive and retain at least one USB port, a water protected circuit board located remotely from the USB port(s) and electrically and communicatively connected to the USB port(s). The USB connection system additionally comprises a laterally rotatable slide-away cover that is pivotally connected to the module via a pivot pin longitudinally disposed within a module housing such that the cover can be laterally rotated, between an opened and a closed position about the pivot pin. Furthermore, in various implementations, the module includes at least one water drainage channel structured and operable to drain water away from the USB port(s).

公开(公告)号：US09638048B2

公开(公告)日：2017-05-02

申请号：US13840881

申请日：2013-03-15

Applicant: Bell Helicopter Textron Inc.

Inventor： Ronald J. Measom ,  James R. Stamper, Jr. ,  Robert Self ,  Paul Sherrill ,  Paul Oldroyd ,  Neil Edward Morrow ,  Russell Cole

IPC: B29C41/00 ,  F01D5/28 ,  B29C70/34 ,  B29C70/46 ,  B29C70/54 ,  B23P15/04

CPC classification number: B29C70/342 ,  B23P15/04 ,  B29C70/46 ,  B29C70/541 ,  B29K2063/00 ,  B29K2105/0881 ,  B29K2307/04 ,  B29L2031/082 ,  B64C27/473 ,  B64C2027/4736 ,  B64F5/10 ,  F01D5/282 ,  Y10T29/49337

Abstract: A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.

公开(公告)号：US20170089449A1

公开(公告)日：2017-03-30

申请号：US14870170

申请日：2015-09-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Eric Stephen Olson

IPC: F16H57/04 ,  F16H55/17

CPC classification number: F16H57/0431 ,  B64C27/12 ,  F16H55/17 ,  F16H57/0423 ,  F16H57/0426 ,  F16H57/043 ,  F16H57/0442 ,  F16H57/0479 ,  F16H57/0486 ,  F16H57/0495

Abstract: In some embodiments, a gear includes a toothed portion that has a plurality of teeth, an inner wall that defines a cavity, and a lubricant feed aperture. The lubricant feed aperture extends from the inner wall portion to the toothed portion. The lubricant feed aperture can deliver lubricant from the cavity to the toothed portion.

公开(公告)号：US20170067814A1

公开(公告)日：2017-03-09

申请号：US14844865

申请日：2015-09-03

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Alan H. Steinert

IPC: G01N15/08 ,  G08B21/18 ,  B01D46/42 ,  B64C27/14 ,  B01D46/44

CPC classification number: G01N15/0826 ,  B01D46/0086 ,  B01D2279/60 ,  B64C27/14 ,  G01N2015/084

Abstract: In one example embodiment, a filter condition measurement device features an engine data repository, one or more sensor units, and a measurement unit. The measurement system is configured to identify a first flow value corresponding to a sensed engine power value from the engine data repository, determine a filter coefficient for the filter as a function of the first flow value and the sensed delta-pressure value; identify a second engine power value from the plurality of stored engine power values and a second flow value corresponding to the second engine power value; and determine a second delta-pressure value for the air filter as a function of the filter coefficient and the second flow value.

Abstract translation: 在一个示例实施例中，过滤条件测量装置具有发动机数据存储库，一个或多个传感器单元和测量单元。 所述测量系统被配置为根据来自所述发动机数据存储库的感测到的发动机功率值来识别对应于所检测到的发动机功率值的第一流量值，根据所述第一流量值和所述检测到的δ压力值确定所述过滤器的过滤器系数; 根据所述多个存储的发动机功率值和对应于所述第二发动机功率值的第二流量值识别第二发动机功率值; 并且根据滤波器系数和第二流量值确定空气过滤器的第二增量压力值。

公开(公告)号：US09574497B2

公开(公告)日：2017-02-21

申请号：US14048973

申请日：2013-10-08

Applicant: Bell Helicopter Textron Inc.

Inventor： Zachary Dailey ,  Thomas Mast

IPC: F02C7/04 ,  B64D33/02

CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0246 ,  Y10T137/0536

Abstract: One example of an engine mounted inlet plenum for a rotorcraft includes an inlet flange, an outlet flange and a plenum duct that connects the inlet flange and the outlet flange. The inlet flange, which defines an inlet to flow air into a barrier filtration system, is configured to be substantially aligned with a closed cowl door assembly of the rotorcraft. In some implementations, the plenum duct is configured to extend to an outer mold line (OML) of the rotorcraft such that the inlet flange is aligned with the OML. The outlet flange defines an outlet to flow air filtered by the barrier filtration system into an engine of the rotorcraft. The plenum duct allows air to flow from the inlet to the outlet.

Abstract translation: 用于旋翼飞机的发动机安装的入口增压室的一个示例包括入口法兰，出口法兰和连接入口法兰和出口法兰的通风管。 限定将空气流入阻挡物过滤系统的入口的入口法兰被构造成与旋翼航空器的封闭整流罩门组件大致对准。 在一些实施方式中，增压通道构造成延伸到旋翼飞行器的外模线（OML），使得入口凸缘与OML对准。 出口法兰限定出口，用于将由隔离物过滤系统过滤的空气流入旋翼航空器的发动机。 通风管允许空气从入口流到出口。

公开(公告)号：US09567091B2

公开(公告)日：2017-02-14

申请号：US14297159

申请日：2014-06-05

Applicant: Bell Helicopter Textron Inc.

Inventor： Joseph M. Schaeffer ,  Jignesh Patel ,  Eric O'Neill

IPC: B64D31/00 ,  B64C19/00 ,  G05D1/00 ,  B64C27/54 ,  B64C27/57

CPC classification number: B64D31/00 ,  B64C19/00 ,  B64C27/54 ,  B64C27/57 ,  G05D1/0072

Abstract: A method of preserving rotor speed during a one engine inoperative operation of an rotorcraft, the method can include: detecting a failure of a first engine; monitoring an engine parameter associated with a second engine; using a computer processor to compare the engine parameter to an engine limit; and commanding a decrease collective pitch command when the engine parameter is within a predefined range of the engine limit.

Abstract translation: 一种在旋转飞机的一个发动机不工作的操作期间保持转子速度的方法，所述方法可以包括：检测第一发动机的故障; 监测与第二发动机相关联的发动机参数; 使用计算机处理器将发动机参数与发动机限制进行比较; 并且当所述发动机参数在所述发动机限制的预定义范围内时，命令减小集体俯仰命令。

公开(公告)号：US20170036759A1

公开(公告)日：2017-02-09

申请号：US14817442

申请日：2015-08-04

Applicant: Bell Helicopter Textron Inc.

Inventor： Drew Sutton ,  Paul K. Oldroyd ,  James Braswell, JR. ,  Scott Wolthuis ,  Paul Sherrill

IPC: B64C27/473

CPC classification number: B64C27/473 ,  B64C2027/4736

Abstract: A rotorcraft rotor blade assembly includes an upper skin portion extending substantially a full span of the rotor blade assembly and a lower skin portion extending substantially the full span of the rotor blade assembly. Each of the upper skin portion and the lower skin portion is configured to carry at least substantially 30% of rotor blade assembly loads.

Abstract translation: 旋翼航空器转子叶片组件包括基本上延伸的转子叶片组件的整个跨度的上部皮肤部分和基本上延伸的转子叶片组件的整个跨度的下部皮肤部分。 上皮肤部分和下皮肤部分中的每一个构造成承载至少基本上30％的转子叶片组件负载。

公开(公告)号：US09550347B2

公开(公告)日：2017-01-24

申请号：US13955105

申请日：2013-07-31

Applicant: Bell Helicopter Textron Inc.

Inventor： Phillip A. Kendrick ,  Paul K. Oldroyd ,  David G. Carlson

IPC: B32B37/00 ,  B32B37/14 ,  B32B3/12 ,  B64C1/18 ,  B64C3/20 ,  B32B5/14 ,  B29D99/00 ,  B29C65/48 ,  B29C65/78 ,  B32B5/12 ,  B32B7/12 ,  B32B3/04 ,  B32B38/00 ,  B29L31/30 ,  B29L31/60 ,  B29C65/00 ,  B29C65/50

CPC classification number: B32B37/146 ,  B29C65/483 ,  B29C65/4835 ,  B29C65/486 ,  B29C65/5042 ,  B29C65/5057 ,  B29C65/7838 ,  B29C66/0042 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/5227 ,  B29C66/54 ,  B29C66/612 ,  B29C66/71 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/72143 ,  B29C66/7254 ,  B29C66/7392 ,  B29C66/7394 ,  B29C66/8122 ,  B29C66/81261 ,  B29C66/81467 ,  B29C66/8185 ,  B29C66/8284 ,  B29C66/83415 ,  B29D99/0021 ,  B29L2031/3076 ,  B29L2031/3088 ,  B29L2031/608 ,  B32B3/04 ,  B32B3/12 ,  B32B5/12 ,  B32B5/142 ,  B32B7/12 ,  B32B2038/0076 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2307/302 ,  B32B2605/00 ,  B32B2605/18 ,  B64C1/18 ,  B64C3/20 ,  Y10T156/1093 ,  Y10T428/24149 ,  Y10T428/24165 ,  B29K2827/18 ,  B29K2307/04 ,  B29K2077/00 ,  B29K2309/08 ,  B29K2277/10 ,  B29K2071/00 ,  B29K2067/00 ,  B29K2061/00 ,  B29K2081/04 ,  B29K2063/00 ,  B29K2079/08 ,  B29K2031/00 ,  B29K2061/04

Abstract: A method of manufacturing a core stiffened structure includes orienting the plurality of core wafers in a non-uniform pattern onto a first face sheet, the non-uniform pattern producing non-uniform spacing between adjacent core wafers; assembling a second face sheet onto the plurality of wafers; and curing an adhesive to create a bond between the plurality of wafers, the first face sheet, and the second face sheet.

Abstract translation: 一种制造芯加强结构的方法包括以非均匀图案将多个芯晶片定向到第一面板上，该不均匀图案产生相邻芯片之间的不均匀间隔; 将第二面板组装到所述多个晶片上; 以及固化粘合剂以在所述多个晶片，所述第一面板和所述第二面板之间产生粘合。