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    Fluid transfer chamber for aircraft fluid transmission lines
    1.
    发明授权
    Fluid transfer chamber for aircraft fluid transmission lines 有权
    用于飞机流体传输线的流体传送室

    公开(公告)号：US09340279B2

    公开(公告)日：2016-05-17

    申请号：US14267160

    申请日：2014-05-01

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Joseph Leachman

    IPC: B64D37/02 ,  B64C17/10 ,  B64D37/00

    CPC classification number: B64C17/10 ,  B64C1/1453 ,  B64D37/00 ,  B64D37/005 ,  B64D37/32 ,  F16L55/07 ,  Y02T50/44 ,  Y10T137/6906

    Abstract: One example of an aircraft fuel transfer chamber includes a chamber housing including a first sub-chamber defining a first inlet to be connected to an outer tube of a first aircraft fuel line assembly. The first sub-chamber receives fuel leaked into the outer tube of the first aircraft fuel line assembly from an inner tube of the first aircraft fuel line assembly. The chamber housing also includes a second sub-chamber connected to the first sub-chamber, the second sub-chamber defining a second inlet to be connected to an outer tube of a second aircraft fuel line assembly. The second sub-chamber receives fuel leaked into the outer tube of the second aircraft fuel line assembly from an inner tube of the second aircraft fuel line assembly. The chamber housing defines an outlet connected to the first inlet and the second inlet to transfer leaked fuel toward a drain of the aircraft.

    Abstract translation: 飞机燃料传递室的一个示例包括腔室壳体，其包括限定要连接到第一飞行器燃料管路组件的外管的第一入口的第一子室。 第一子室从第一飞行器燃料管路组件的内管接收从第一飞行器燃料管路组件的外管泄漏的燃料。 腔室壳体还包括连接到第一子室的第二子室，第二子室限定要连接到第二飞行器燃料管路组件的外管的第二入口。 第二子室从第二飞行器燃料管路组件的内管接收泄漏到第二飞行器燃料管路组件的外管中的燃料。 腔室壳体限定了连接到第一入口和第二入口的出口，以将泄漏的燃料转移到飞行器的排水口。

    Adapter for aircraft fluid transmission lines
    3.
    发明授权
    Adapter for aircraft fluid transmission lines 有权
    飞机流体输送线适配器

    公开(公告)号：US09592919B2

    公开(公告)日：2017-03-14

    申请号：US14250583

    申请日：2014-04-11

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Joseph Leachman

    IPC: F16L9/00 ,  F16L11/00 ,  B64D37/00 ,  B64C29/00 ,  F16L7/00

    CPC classification number: B64D37/005 ,  B64C29/0033 ,  F16L7/00 ,  Y02T50/44

    Abstract: One example of an aircraft fuel line assembly clamp member includes a c-shaped outer shell and a plurality of spokes. The c-shaped outer shell is sized to be positioned within an outer tube of an aircraft fuel line assembly. The plurality of spokes is arranged on an inner surface of the outer shell. The plurality of spokes protrudes from the inner surface towards a center of the outer shell to define a shape to receive an inner tube of the aircraft fuel line assembly. The plurality of spokes is also spaced apart on the inner surface.

    Abstract translation: 飞机燃料管路组件夹紧构件的一个实例包括c形外壳和多个轮辐。 c形外壳的尺寸设置成定位在飞行器燃料管线组件的外管内。 多个轮辐布置在外壳的内表面上。 多个轮辐从内表面朝向外壳的中心突出以限定用于接收飞行器燃料管路组件的内管的形状。 多个轮辐也在内表面上间隔开。

    Integrated emergency egress equipment
    5.
    发明授权
    Integrated emergency egress equipment 有权

    公开(公告)号：US11110304B2

    公开(公告)日：2021-09-07

    申请号：US15861827

    申请日：2018-01-04

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Joseph Leachman

    IPC: A62B1/16 ,  B64C27/00 ,  B64D11/06 ,  B64D25/08 ,  B64D47/02

    Abstract: The present invention includes an emergency egress system of a vehicle, including: a rope compartment, wherein the rope compartment is located on or near a vertical plane along a longitudinal axis of the vehicle, within reach of one or more occupant seats; a rope, wherein at least a portion of the rope is stored within the rope compartment and is securely tethered to a portion of a structure of the vehicle; and a rope compartment cover to secure the rope in the rope compartment.

    INTEGRATED EMERGENCY EGRESS EQUIPMENT
    6.
    发明申请
    INTEGRATED EMERGENCY EGRESS EQUIPMENT 审中-公开

    公开(公告)号：US20190118006A1

    公开(公告)日：2019-04-25

    申请号：US15861827

    申请日：2018-01-04

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Joseph Leachman

    IPC: A62B1/16 ,  B64D11/06 ,  B64C27/00

    Abstract: The present invention includes an emergency egress system of a vehicle, including: a rope compartment, wherein the rope compartment is located on or near a vertical plane along a longitudinal axis of the vehicle, within reach of one or more occupant seats; a rope, wherein at least a portion of the rope is stored within the rope compartment and is securely tethered to a portion of a structure of the vehicle; and a rope compartment cover to secure the rope in the rope compartment.

    FLUID TRANSFER CHAMBER FOR AIRCRAFT FLUID TRANSMISSION LINES
    8.
    发明申请
    FLUID TRANSFER CHAMBER FOR AIRCRAFT FLUID TRANSMISSION LINES 有权
    用于飞机流体传输线的流体传送室

    公开(公告)号：US20150314858A1

    公开(公告)日：2015-11-05

    申请号：US14267160

    申请日：2014-05-01

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Joseph Leachman

    IPC: B64C17/10 ,  B64D37/00

    CPC classification number: B64C17/10 ,  B64C1/1453 ,  B64D37/00 ,  B64D37/005 ,  B64D37/32 ,  F16L55/07 ,  Y02T50/44 ,  Y10T137/6906

    Abstract: One example of an aircraft fuel transfer chamber includes a chamber housing including a first sub-chamber defining a first inlet to be connected to an outer tube of a first aircraft fuel line assembly. The first sub-chamber receives fuel leaked into the outer tube of the first aircraft fuel line assembly from an inner tube of the first aircraft fuel line assembly. The chamber housing also includes a second sub-chamber connected to the first sub-chamber, the second sub-chamber defining a second inlet to be connected to an outer tube of a second aircraft fuel line assembly. The second sub-chamber receives fuel leaked into the outer tube of the second aircraft fuel line assembly from an inner tube of the second aircraft fuel line assembly. The chamber housing defines an outlet connected to the first inlet and the second inlet to transfer leaked fuel toward a drain of the aircraft.

    Abstract translation: 飞机燃料传递室的一个示例包括腔室壳体，其包括限定要连接到第一飞行器燃料管路组件的外管的第一入口的第一子室。 第一子室从第一飞行器燃料管路组件的内管接收从第一飞行器燃料管路组件的外管泄漏的燃料。 腔室壳体还包括连接到第一子室的第二子室，第二子室限定要连接到第二飞行器燃料管路组件的外管的第二入口。 第二子室从第二飞行器燃料管路组件的内管接收泄漏到第二飞行器燃料管路组件的外管中的燃料。 腔室壳体限定了连接到第一入口和第二入口的出口，以将泄漏的燃料转移到飞行器的排水口。

    Adapter for Aircraft Fluid Transmission Lines
    9.
    发明申请
    Adapter for Aircraft Fluid Transmission Lines 有权
    飞机流体输送线适配器

    公开(公告)号：US20150291290A1

    公开(公告)日：2015-10-15

    申请号：US14250583

    申请日：2014-04-11

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Joseph Leachman

    IPC: B64D37/00 ,  B64D37/32 ,  F16L3/08

    CPC classification number: B64D37/005 ,  B64C29/0033 ,  F16L7/00 ,  Y02T50/44

    Abstract: One example of an aircraft fuel line assembly clamp member includes a c-shaped outer shell and a plurality of spokes. The c-shaped outer shell is sized to be positioned within an outer tube of an aircraft fuel line assembly. The plurality of spokes is arranged on an inner surface of the outer shell. The plurality of spokes protrudes from the inner surface towards a center of the outer shell to define a shape to receive an inner tube of the aircraft fuel line assembly. The plurality of spokes is also spaced apart on the inner surface.

    Abstract translation: 飞机燃料管路组件夹紧构件的一个实例包括c形外壳和多个轮辐。 c形外壳的尺寸设置成定位在飞行器燃料管线组件的外管内。 多个轮辐布置在外壳的内表面上。 多个轮辐从内表面朝向外壳的中心突出以限定用于接收飞行器燃料管路组件的内管的形状。 多个轮辐也在内表面上间隔开。

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