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    Aircraft component
    101.
    发明授权
    Aircraft component 有权
    飞机部件

    公开(公告)号：US08276846B2

    公开(公告)日：2012-10-02

    申请号：US11762342

    申请日：2007-06-13

    Applicant: James Lloyd

    Inventor： James Lloyd

    IPC: B64C1/00

    CPC classification number: B64C1/064 ,  B64C1/065

    Abstract: An aircraft component includes a composite laminate structure, the composite laminate structure including an end surface at which a multiplicity of the layers of the laminate structure terminate. The aircraft component further includes a deflecting surface mounted to the composite laminate structure for protecting the end surface from direct impacts. In one embodiment, the end surface of the composite laminate structure has a convex cross-section and the deflecting surface includes laminate material laid over the end surface. In a further embodiment, the deflecting surface includes an inert strip.

    Abstract translation: 飞机部件包括复合层压结构，复合层压结构包括层叠结构的多个层终止的端面。 飞机部件还包括安装到复合层压结构的偏转表面，用于保护端面不受直接冲击。 在一个实施例中，复合层压结构的端面具有凸的横截面，并且偏转表面包括铺设在端表面上的层压材料。 在另一个实施例中，偏转表面包括惰性条带。

    Composite aircraft component
    102.
    发明授权
    Composite aircraft component 有权
    复合飞机部件

    公开(公告)号：US07942368B2

    公开(公告)日：2011-05-17

    申请号：US11762362

    申请日：2007-06-13

    Applicant: James Lloyd

    Inventor： James Lloyd

    IPC: B64C1/00 ,  B64C3/00

    CPC classification number: B64C3/185 ,  B64C1/064 ,  B64C1/065 ,  B64C3/182 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T156/10

    Abstract: This invention relates to improving the tolerance of composite laminate structures to damage and/or delamination, resulting in weakening of the structure and/or to reducing the possibility of such damage and/or delamination. In particular, but not exclusively the invention relates to protecting the end surfaces of composite laminate structures present on aircraft from impact damage. The invention provides an aircraft component comprising a composite laminate structure, the composite laminate structure including an end surface at which a multiplicity of the layers of the laminate structure terminate, wherein the aircraft component further comprises a deformable strip mounted to protect the end surface of the composite laminate structure from direct impacts.

    Abstract translation: 本发明涉及改善复合层压结构损坏和/或分层的公差，导致结构变薄和/或降低这种损坏和/或分层的可能性。 特别地但并非排他性地，本发明涉及保护飞机上存在的复合层压结构的端面免受冲击损坏。 本发明提供了一种包括复合层压结构的飞行器部件，该复合层压结构包括端面，层压结构的多个层终止于该端面，其中飞行器部件还包括可变形条，其安装以保护该层压结构的端面 复合层压结构从直接影响。

    COMPOSITE STRUCTURE
    103.
    发明申请
    COMPOSITE STRUCTURE 有权
    复合结构

    公开(公告)号：US20100068450A1

    公开(公告)日：2010-03-18

    申请号：US12513402

    申请日：2007-11-26

    Applicant: James Lloyd

    Inventor： James Lloyd

    IPC: B32B3/06 ,  B32B3/00 ,  B32B37/00

    CPC classification number: B32B3/02 ,  B64C1/12 ,  B64C3/24 ,  B64C3/26 ,  Y10T156/10 ,  Y10T428/24008 ,  Y10T428/24479 ,  Y10T428/24612

    Abstract: A composite structure comprising: a panel formed from two or more plies of composite material, the panel having a surface formed with a step where the thickness of the panel changes. Two or more stiffeners are attached to the surface of the panel. One of the stiffeners engages at least part of the step so as to transmit load forces in the panel.

    Abstract translation: 一种复合结构，包括：由两层或多层复合材料形成的板，所述板具有形成有所述板的厚度改变的台阶的表面。 两个或多个加强件连接到面板的表面。 加强件中的一个与工作台的至少一部分接合，以便传递面板中的载荷力。

    COMPOSITE AIRCRAFT COMPONENT
    104.
    发明申请
    COMPOSITE AIRCRAFT COMPONENT 有权
    复合飞机组件

    公开(公告)号：US20080308669A1

    公开(公告)日：2008-12-18

    申请号：US11762362

    申请日：2007-06-13

    Applicant: James LLOYD

    Inventor： James LLOYD

    IPC: B64C3/20 ,  B64C39/00

    CPC classification number: B64C3/185 ,  B64C1/064 ,  B64C1/065 ,  B64C3/182 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T156/10

    Abstract: This invention relates to improving the tolerance of composite laminate structures to damage and/or delamination, resulting in weakening of the structure and/or to reducing the possibility of such damage and/or delamination. In particular, but not exclusively the invention relates to protecting the end surfaces of composite laminate structures present on aircraft from impact damage. The invention provides an aircraft component comprising a composite laminate structure, the composite laminate structure including an end surface at which a multiplicity of the layers of the laminate structure terminate, wherein the aircraft component further comprises a deformable strip mounted to protect the end surface of the composite laminate structure from direct impacts.

    Abstract translation: 本发明涉及改善复合层压结构损坏和/或分层的公差，导致结构变薄和/或降低这种损坏和/或分层的可能性。 特别地但并非排他性地，本发明涉及保护飞机上存在的复合层压结构的端面免受冲击损坏。 本发明提供了一种包括复合层压结构的飞行器部件，该复合层压结构包括端面，层压结构的多个层终止于该端面，其中飞行器部件还包括可变形条，其安装以保护该层压结构的端面 复合层压结构从直接影响。

    Detachable magnetic electrical connector
    106.
    发明申请
    Detachable magnetic electrical connector 审中-公开
    可拆卸磁性电连接器

    公开(公告)号：US20070161262A1

    公开(公告)日：2007-07-12

    申请号：US11327797

    申请日：2006-01-06

    Applicant: James Lloyd

    Inventor： James Lloyd

    IPC: H01R11/30

    CPC classification number: H01R13/6205 ,  H01R13/652

    Abstract: A connector body (10) attached to an appliance has a first body (12) with four contact receptacles (24-30) and a magnet (20, 22) which is adapted to attach and detach from a second body (14) having four contact pins (34-40) and a ferrous metal plate (32). The second body (14) is attached to an electrical cord (16) with a grounded plug (18). Two of the pins are the live electrical connections, and the other two pins are ground connections, co-existing so that as long as one remains in contact the grounded connection for the appliance exists. The two ground connections are spatially located relative to one another so that no matter which direction break-away occurs, at least one will always be in connection until the live connection is broken first.

    Abstract translation: 附接到器具的连接器主体（10）具有第一主体（12），其具有四个接触插座（24-30）和磁体（20,22），该磁体适于从具有四个的第二主体（14） 接触销（34-40）和黑色金属板（32）。 第二主体（14）用接地插头（18）连接到电线（16）。 两个引脚是带电电气连接，另外两个引脚是接地连接，共同存在，只要一个引脚保持接触，就存在用于器具的接地连接。 两个接地连接在空间上相对于彼此定位，使得无论发生哪个方向分离，至少一个将始终连接，直到活动连接首先断开。

    Adaptive inflation mechanism
    109.
    发明授权
    Adaptive inflation mechanism 有权

    公开(公告)号：US06409213B1

    公开(公告)日：2002-06-25

    申请号：US09866366

    申请日：2001-05-25

    Applicant: James Lloyd Webber ,  Robert Lee Jones

    Inventor： James Lloyd Webber ,  Robert Lee Jones

    IPC: B60R2130

    Abstract: This present invention provides variable deployment performance by controlling the quantity and fluid flow path of the inflator gas into or out of an air bag module according to the present invention. The air bag module includes a slide ring mechanism disposed about an inflator and adjacent at least a portion of a cushion retainer. The slide ring mechanism comprises an annular ring having openings formed therein, wherein during rotation of the slide mechanism, the openings of the annular ring align with openings formed in the cushion retainer to define a fluid flow path away from an air bag cushion for venting some of the inflator gas. Preferably, the annular ring is rotated by attaching a pair of tethers to the annular ring and to a rear surface of the air bag cushion. As the air bag cushion inflates and reaches a predetermined pressure, the tethers are pulled causing the slide ring to rotate so that the openings in the annular ring and cushion retainer align directing an amount of inflator gas away from the air bag cushion. The present invention thus provides a direct mechanical system for cushion pressure feedback to tailor the inflation.

    Seat restraint tensioner
    110.
    发明授权
    Seat restraint tensioner 失效

    公开(公告)号：US06340176B1

    公开(公告)日：2002-01-22

    申请号：US09540623

    申请日：2000-03-31

    Applicant: James Lloyd Webber ,  Lloyd Walker Rogers, Jr.

    Inventor： James Lloyd Webber ,  Lloyd Walker Rogers, Jr.

    IPC: B60R2246

    CPC classification number: B60R22/1952 ,  B60R22/1955

    Abstract: A seat restraint tensioner for a seat restraint system in a vehicle includes a housing for operative connection to vehicle structure and a movable piston disposed in the housing. The seat restraint tensioner also includes a gas generator operatively connected to the housing for expelling a gas to move the piston. The piston includes a passageway extending therethrough to control a rate of stroke of the piston when the gas is generated to apply a force for pulling-down belt webbing of the seat restraint system.

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