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    Nose landing gear arrangements and methods for making the same
    2.
    发明授权
    Nose landing gear arrangements and methods for making the same 有权
    鼻子起落架布置和制作方法

    公开(公告)号：US09290263B2

    公开(公告)日：2016-03-22

    申请号：US14201345

    申请日：2014-03-07

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Brian Cook ,  John Louis ,  Thomas Van de Ven ,  Robert M. Vieito ,  Mehdi R. Khorrami

    IPC: B64C25/10 ,  B64C25/16 ,  B64C23/00 ,  B64C25/00 ,  B64C25/04 ,  B64C25/18

    CPC classification number: B64C25/16 ,  B64C23/005 ,  B64C25/001 ,  B64C25/04 ,  B64C25/18 ,  B64C2025/003 ,  Y10T29/4984

    Abstract: Nose landing gear arrangements including a folding follow-up door for reducing airflow noise for aircrafts, aircrafts including such nose landing gear arrangements, and methods for making such nose landing gear arrangements are provided herein. In one example, a nose landing gear arrangement includes a wheel assembly and a main strut. The main strut is operatively coupled to the wheel assembly and is configured to extend outside of the fuselage substantially along a generally vertical plane. A folding follow-up door is pivotally coupled to the main strut and extends to the fuselage. The folding follow-up door includes a first door section and a second door section that extend outwardly in directions away from each other to define an unfolded position. The folding follow-up door is foldable to move the first and second door sections towards each other about the generally vertical plane to define a folded position.

    Abstract translation: 这里提供了包括用于减少飞行器的气流噪声的折叠后跟门，包括这种前起落架装置的飞机以及用于制造这种前起落架装置的方法的鼻子起落架布置。 在一个示例中，前起落架布置包括车轮组件和主支柱。 主支柱可操作地联接到车轮组件并且构造成基本上沿着大致垂直的平面延伸到机身的外部。 折叠的后跟门枢转地连接到主支柱并延伸到机身。 折叠后续门包括第一门部分和第二门部分，该第一门部分和第二门部分沿彼此远离的方向向外延伸以限定展开位置。 折叠后续门是可折叠的，以使第一和第二门部分围绕大致垂直的平面朝向彼此移动以限定折叠位置。

    NOSE LANDING GEAR ARRANGEMENTS AND METHODS FOR MAKING THE SAME
    5.
    发明申请
    NOSE LANDING GEAR ARRANGEMENTS AND METHODS FOR MAKING THE SAME 有权
    NOSE接地齿轮安装及其制造方法

    公开(公告)号：US20150251750A1

    公开(公告)日：2015-09-10

    申请号：US14201345

    申请日：2014-03-07

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Brian Cook ,  John Louis ,  Thomas Van de Ven ,  Robert M. Vieito ,  Mehdi R. Khorrami

    IPC: B64C25/16 ,  B64C25/18 ,  B64C25/04 ,  B64C23/00 ,  B64C25/00

    CPC classification number: B64C25/16 ,  B64C23/005 ,  B64C25/001 ,  B64C25/04 ,  B64C25/18 ,  B64C2025/003 ,  Y10T29/4984

    Abstract: Nose landing gear arrangements including a folding follow-up door for reducing airflow noise for aircrafts, aircrafts including such nose landing gear arrangements, and methods for making such nose landing gear arrangements are provided herein. In one example, a nose landing gear arrangement includes a wheel assembly and a main strut. The main strut is operatively coupled to the wheel assembly and is configured to extend outside of the fuselage substantially along a generally vertical plane. A folding follow-up door is pivotally coupled to the main strut and extends to the fuselage. The folding follow-up door includes a first door section and a second door section that extend outwardly in directions away from each other to define an unfolded position. The folding follow-up door is foldable to move the first and second door sections towards each other about the generally vertical plane to define a folded position

    Abstract translation: 这里提供了包括用于减少飞行器的气流噪声的折叠后跟门，包括这种前起落架装置的飞机以及用于制造这种前起落架装置的方法的鼻子起落架布置。 在一个示例中，前起落架布置包括车轮组件和主支柱。 主支柱可操作地联接到车轮组件并且构造成基本上沿着大致垂直的平面延伸到机身的外部。 折叠的后跟门枢转地连接到主支柱并延伸到机身。 折叠后续门包括第一门部分和第二门部分，该第一门部分和第二门部分沿彼此远离的方向向外延伸以限定展开位置。 折叠后续门是可折叠的，以使第一和第二门部分围绕大体上垂直的平面朝向彼此移动以限定折叠位置

    PROPULSION SYSTEM FOR AN AIRCRAFT AND METHOD OF MANUFACTURING A PROPULSION SYSTEM FOR AN AIRCRAFT
    7.
    发明申请
    PROPULSION SYSTEM FOR AN AIRCRAFT AND METHOD OF MANUFACTURING A PROPULSION SYSTEM FOR AN AIRCRAFT 有权

    公开(公告)号：US20210025352A1

    公开(公告)日：2021-01-28

    申请号：US16522463

    申请日：2019-07-25

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Donald Freund ,  Michael Rybalko ,  Joseph R. Gavin ,  John Louis

    IPC: F02K1/15

    Abstract: A propulsion system for an aircraft is taught herein. The propulsion system includes, but is not limited to, an engine that is configured to produce a gas jet. The propulsion system further includes a nozzle that is coupled with the engine and that is disposed to receive the gas jet. The nozzle has a throat that is configured to expand and contract. The propulsion system still further includes a controller that is operatively coupled with the throat. The controller is configured to control the throat to expand and contract and to control a magnitude of a thrust imparted by the gas jet by controlling the throat to expand and contract. The controller is further configured to control the magnitude of the thrust by controlling the throat to expand and contract when the aircraft is flying at or above the local speed of sound.

    Nose landing gear arrangement for aircraft and method of assembly
    9.
    发明授权
    Nose landing gear arrangement for aircraft and method of assembly 有权
    用于飞机的鼻子起落架布置和组装方法

    公开(公告)号：US09302767B2

    公开(公告)日：2016-04-05

    申请号：US13674303

    申请日：2012-11-12

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Brian G. Cook ,  John Louis ,  Thomas Van de Ven ,  Robert M. Vieito

    IPC: B64C25/00 ,  B64C25/16 ,  B64C25/14

    CPC classification number: B64C25/001 ,  B64C25/14 ,  B64C25/16 ,  B64C2025/003 ,  B64C2025/006 ,  Y10T29/49826

    Abstract: A nose landing gear arrangement for an aircraft and a method of assembling the nose landing gear arrangement are disclosed herein. The nose landing gear arrangement includes, but is not limited to, a wheel assembly, a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft, and a torque arm assembly coupled to the wheel assembly and to the shock strut. The torque arm assembly is configured to transmit torque to the wheel assembly. The torque arm assembly is disposed forward of the shock strut with respect to a direction of travel of the aircraft.

    Abstract translation: 本文公开了一种用于飞行器的前起落架装置和组装前起落架装置的方法。 前起落架装置包括但不限于轮组件，从车轮组件向上延伸到飞行器的机身的冲击支柱，以及联接到车轮组件和冲击支柱的扭矩臂组件。 扭矩臂组件构造成将扭矩传递到车轮组件。 扭矩臂组件相对于飞行器的行进方向设置在冲击支柱的前方。

    WING FLAPS FOR AIRCRAFT AND METHODS FOR MAKING THE SAME
    10.
    发明申请
    WING FLAPS FOR AIRCRAFT AND METHODS FOR MAKING THE SAME 有权
    飞机用飞轮及其制造方法

    公开(公告)号：US20140209737A1

    公开(公告)日：2014-07-31

    申请号：US13752654

    申请日：2013-01-29

    Applicant: GULFSTREAM AEROSPACE CORPORATION

    Inventor： Brian G. Cook ,  John Louis ,  Thomas Van de Van ,  Robert M. Vieito

    IPC: B64C1/40

    CPC classification number: B64C7/00 ,  B64C1/40 ,  B64C9/18 ,  Y10T29/49826

    Abstract: Flaps for operatively coupling to wing main elements of aircraft, aircraft including such flaps and methods for making such flaps are provided herein. In one example, a flap for operatively coupling to a wing main element of an aircraft comprises an outer flap section that has a side edge portion. The side edge portion at least partially surrounds a flap side-edge cavity. A porous cavity-filler insert is positioned in the flap side-edge cavity.

    Abstract translation: 本文提供了用于可操作地联接到飞行器的机翼主要元件的翼片，包括这种翼片的飞行器和用于制造这种翼片的方法。 在一个示例中，用于可操作地联接到飞行器的机翼主元件的翼片包括具有侧边缘部分的外翼片部分。 侧边缘部分至少部分地围绕翼片侧边缘腔。 多孔空腔 - 填料插入件位于翼片侧边缘腔中。

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