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    FUSELAGE-MOUNTED LANDING GEAR ASSEMBLY FOR USE WITH A LOW WING AIRCRAFT
    1.
    发明申请
    FUSELAGE-MOUNTED LANDING GEAR ASSEMBLY FOR USE WITH A LOW WING AIRCRAFT 审中-公开
    用于低空飞机的FUSELAGE-MOUNTED LANDING GEAR ASSEMBLY FOR USE

    公开(公告)号：US20150069178A1

    公开(公告)日：2015-03-12

    申请号：US14021301

    申请日：2013-09-09

    Applicant: The Boeing Company

    Inventor： Stephen T. Brown ,  Michael Lane Drake ,  Christopher R. Holtorf ,  Justin Cottet

    IPC: B64C25/12

    CPC classification number: B64C25/12 ,  B64C2025/125

    Abstract: An aircraft comprises at least one wing comprising a trailing edge flap that is selectively moveable between a stowed position and an extended position. The aircraft also includes a fuselage comprising a first gear door on a side of the fuselage and a second gear door on a bottom of the fuselage. The first gear door is moveable in a gear door envelope between a closed position and an open position. The wing is coupled to the fuselage in a low-wing configuration. A landing gear assembly is coupled to the fuselage and is selectively moveable between a retracted position and a deployed position. The trailing edge flap may be extended simultaneously with, before, or after deployment of the landing gear assembly and opening of the first gear door.

    Abstract translation: 一种飞行器包括至少一个翼片，其包括可在收起位置和延伸位置之间选择性地移动的后缘翼片。 飞机还包括一个机身，其中包括在机身侧面的第一齿轮门和在机身底部的第二齿轮门。 第一个齿轮门可以在一个闭合位置和一个打开位置之间的一个齿轮门壳中移动。 机翼以低翼配置耦合到机身。 起落架组件联接到机身，并且可以在缩回位置和展开位置之间选择性地移动。 后缘襟翼可以与起落架组件展开同时延伸，也可以在第一档门打开后展开。

    VARIABLE GEOMETRY AERODYNAMIC BLADE WITH INTEGRAL SHAPE MEMORY ACTUATION
    2.
    发明申请
    VARIABLE GEOMETRY AERODYNAMIC BLADE WITH INTEGRAL SHAPE MEMORY ACTUATION 有权

    公开(公告)号：US20210131295A1

    公开(公告)日：2021-05-06

    申请号：US16669766

    申请日：2019-10-31

    Applicant: The Boeing Company

    Inventor： Stephen T. Brown ,  Frederick T. Calkins ,  Sergey D. Barmichev ,  Matthew Naimi

    IPC: F01D7/00 ,  F01D5/28 ,  F01D5/14

    Abstract: A variable geometry aerodynamic blade system employs a blade having a leading edge and a trailing edge. At least one shape memory alloy component is integrated in the blade for aerodynamic repositioning of one or both of the leading and trailing edges. At least one heating element interacts with the at least one shape memory alloy component to provide heating for transition between an austenitic and a martensitic phase. The at least one shape memory alloy component is responsive to the at least one heating element to alter one of a camber and twist of the blade responsive to a control signal. A control system is operatively engaged to the at least one heating element, the control system receiving a command signal and outputting the control signal responsive to the command signal.

    Hybrid turbine jet engines and methods of operating the same
    3.
    发明授权
    Hybrid turbine jet engines and methods of operating the same 有权

    公开(公告)号：US10378452B1

    公开(公告)日：2019-08-13

    申请号：US15904838

    申请日：2018-02-26

    Applicant: The Boeing Company

    Inventor： Sergey D. Barmichev ,  Mark E. Howe ,  Stephen T. Brown

    IPC: F02C7/36 ,  F02C6/14 ,  B64D27/10 ,  B64D27/24 ,  H02P17/00 ,  B64D35/08 ,  F16D23/02 ,  B64D27/02

    Abstract: Hybrid turbine engines and methods of operating the same are disclosed herein. The hybrid turbine engines include a first thrust-generating device that includes a turbine with a turbine rotary shaft and a clutch, which includes a clutch input, which is operatively coupled to the turbine rotary shaft, and a clutch output. The clutch defines an engaged state and a disengaged state. The hybrid turbine engines also include a rotary electric machine including a machine rotary shaft that is operatively coupled to the clutch output, a second thrust-generating device that is operatively coupled to the machine rotary shaft, and an electric power system. The rotary electric machine is configured to selectively receive an electric power output from the electric power system, such as to selectively produce additional thrust, and to selectively receive in an input torque from the machine rotary shaft, such as to selectively produce additional electric power.

    Translating Equipment Rack System
    4.
    发明申请
    Translating Equipment Rack System 有权
    翻译设备机架系统

    公开(公告)号：US20150195947A1

    公开(公告)日：2015-07-09

    申请号：US14661872

    申请日：2015-03-18

    Applicant: THE BOEING COMPANY

    Inventor： Andrew John Bayliss ,  Stephen T. Brown ,  Perry Nicholas Rea ,  Kevin Matthew Retz

    IPC: H05K7/18 ,  B64D47/00

    CPC classification number: B64C1/22 ,  B64C1/1446 ,  B64C3/141 ,  B64D43/00 ,  B64D47/00 ,  H05K7/1411 ,  H05K7/18 ,  Y10T292/0802 ,  Y10T292/0807

    Abstract: An apparatus and method comprising a rack and a translation mechanism. The rack may be configured to hold components. The rack may comprise movable rack segments that are movable independently of each other. The translation mechanism may be configured to move a portion of the movable rack segments relative to another portion of the movable rack segments inside a platform such that internal access to at least a portion of the components is provided inside the platform.

    Abstract translation: 一种包括机架和平移机构的装置和方法。 机架可能被配置为保持组件。 机架可以包括可彼此独立移动的可移动齿条段。 平移机构可以被配置为使可移动齿条段的一部分相对于可移动齿条段的另一部分移动到平台内，使得至少部分组件的内部通路设置在平台内。

    HIGH-WING-AIRCRAFT FUSELAGE SUPPORT STRUCTURE
    5.
    发明申请
    HIGH-WING-AIRCRAFT FUSELAGE SUPPORT STRUCTURE 有权
    高空飞行器辅助结构

    公开(公告)号：US20140231586A1

    公开(公告)日：2014-08-21

    申请号：US13769359

    申请日：2013-02-17

    Applicant: The Boeing Company

    Inventor： Stephen T. Brown ,  Sergey Barmichev

    IPC: B64C1/26 ,  B64F5/00

    CPC classification number: B64C1/26 ,  B64C1/061 ,  B64C1/065 ,  B64C1/18 ,  B64C2025/125

    Abstract: A structural support assembly for a high-wing aircraft may include a plurality of columns extending through a passenger compartment of the aircraft having a pair of wings mounted proximate a top of a fuselage. A column upper end of at least one of the columns may be coupled to a center wing box structure adjacent to a rear spar thereof. A column lower end of at least one of the columns may be coupled to a floor substructure.

    Abstract translation: 用于高翼飞机的结构支撑组件可以包括延伸穿过飞行器的乘客舱的多个列，其具有安装在靠近机身顶部的一对翼。 至少一个列的列上端可以与邻近其后部翼梁的中心翼盒结构联接。 至少一个列的列下端可以联接到底板子结构。

    Variable geometry aerodynamic blade with integral shape memory actuation
    6.
    发明授权
    Variable geometry aerodynamic blade with integral shape memory actuation 有权

    公开(公告)号：US11549383B2

    公开(公告)日：2023-01-10

    申请号：US16669766

    申请日：2019-10-31

    Applicant: The Boeing Company

    Inventor： Stephen T. Brown ,  Frederick T. Calkins ,  Sergey D. Barmichev ,  Matthew Naimi

    IPC: F01D7/00 ,  F01D5/14 ,  F01D5/28

    Abstract: A variable geometry aerodynamic blade system employs a blade having a leading edge and a trailing edge. At least one shape memory alloy component is integrated in the blade for aerodynamic repositioning of one or both of the leading and trailing edges. At least one heating element interacts with the at least one shape memory alloy component to provide heating for transition between an austenitic and a martensitic phase. The at least one shape memory alloy component is responsive to the at least one heating element to alter one of a camber and twist of the blade responsive to a control signal. A control system is operatively engaged to the at least one heating element, the control system receiving a command signal and outputting the control signal responsive to the command signal.

    High traction on demand aircraft landing gear system
    7.
    发明授权
    High traction on demand aircraft landing gear system 有权
    高牵引力的飞机起落架系统

    公开(公告)号：US09457895B1

    公开(公告)日：2016-10-04

    申请号：US13874482

    申请日：2013-05-01

    Applicant: The Boeing Company

    Inventor： Sergey Barmichev ,  Kelly L. Boren ,  Stephen T. Brown

    IPC: B64C25/36 ,  B60C11/14

    CPC classification number: B64C25/36 ,  B60C11/14 ,  B60C11/1606 ,  B60C17/06 ,  B60C2200/02 ,  Y10T29/49492

    Abstract: A traction-on-demand landing gear tire control system and methods are presented. An outer tire of an aircraft wheel is depressurized to a depressurized state in response to a non-optimal aircraft landing condition. An inner tire of the aircraft wheel contacts the outer tire in response to the depressurized state, and a plurality of traction studs are deployed to protrude from the outer tire in response to the inner tire contacting the outer tire.

    Abstract translation: 提出了一种牵引式起落架轮胎控制系统和方法。 响应于非最佳飞机着陆情况，飞轮的外轮胎被减压至减压状态。 飞轮的内胎响应于减压状态而接触外轮胎，并且响应于内轮胎与外胎接触而将多个牵引柱展开成从外胎突出。

    HYBRID TURBINE JET ENGINES AND METHODS OF OPERATING THE SAME
    9.
    发明申请
    HYBRID TURBINE JET ENGINES AND METHODS OF OPERATING THE SAME 有权

    公开(公告)号：US20190264617A1

    公开(公告)日：2019-08-29

    申请号：US15904838

    申请日：2018-02-26

    Applicant: The Boeing Company

    Inventor： Sergey D. Barmichev ,  Mark E. Howe ,  Stephen T. Brown

    IPC: F02C7/36 ,  F02C6/14 ,  B64D27/10 ,  B64D27/24 ,  B64D35/08 ,  H02P17/00

    Abstract: Hybrid turbine engines and methods of operating the same are disclosed herein. The hybrid turbine engines include a first thrust-generating device that includes a turbine with a turbine rotary shaft and a clutch, which includes a clutch input, which is operatively coupled to the turbine rotary shaft, and a clutch output. The clutch defines an engaged state and a disengaged state. The hybrid turbine engines also include a rotary electric machine including a machine rotary shaft that is operatively coupled to the clutch output, a second thrust-generating device that is operatively coupled to the machine rotary shaft, and an electric power system. The rotary electric machine is configured to selectively receive an electric power output from the electric power system, such as to selectively produce additional thrust, and to selectively receive in an input torque from the machine rotary shaft, such as to selectively produce additional electric power.

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