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    Overload detection
    15.
    发明授权
    Overload detection 有权
    过载检测

    公开(公告)号：US08650967B2

    公开(公告)日：2014-02-18

    申请号：US12679001

    申请日：2008-09-19

    Applicant: Ian Bennett

    Inventor： Ian Bennett

    IPC: G01M5/00

    CPC classification number: B64C25/00 ,  B64D2045/008 ,  B64F5/60 ,  F16C11/045 ,  F16C17/24 ,  F16C2326/43 ,  G01L5/0071

    Abstract: An overload detecting assembly comprises a first load bearing member (10) adapted to flex laterally in response to a load to be monitored, a second load bearing member (11) spaced from the first under normal load conditions and which is contacted and loaded by the first load bearing member (10) when it is loaded beyond a load limit. Preferably, the first load bearing member (10) has a yield point below the load limit and takes a permanent set once the yield point has been exceeded. A lateral probe (18) cooperates with the first load bearing member as it moves towards the second load bearing member and in turn deflects an indicator member (20) which takes a permanent set when a yield point is exceeded. Ready inspection of the indicator member then reveals whether or not it has been bent.

    Abstract translation: 过载检测组件包括适于响应待监测的负载侧向弯曲的第一承载构件（10），与第一正常负载条件间隔开的第二承载构件（11），其与第一负载承载构件 当第一承载构件（10）被加载超过负载极限时。 优选地，第一承载构件（10）具有低于载荷极限的屈服点，并且一旦超过屈服点就采用永久变形。 横向探头（18）在第一承载构件向第二承载构件移动时与第一承载构件协作，并且当超过屈服点时，使指示构件（20）偏转，该指示构件（20）是永久变形的。 然后，对指示器构件进行准备检查，然后揭示其是否弯曲。

    Landing gear
    16.
    发明授权
    Landing gear 有权
    起落架

    公开(公告)号：US08382032B2

    公开(公告)日：2013-02-26

    申请号：US13333249

    申请日：2011-12-21

    Applicant: Ian Bennett ,  Richard Charles Lang ,  Robert Anthony Menezes

    Inventor： Ian Bennett ,  Richard Charles Lang ,  Robert Anthony Menezes

    IPC: B64C25/10 ,  B64C25/58

    CPC classification number: B64C25/60 ,  B64C25/22 ,  B64C25/34 ,  B64C25/58

    Abstract: A semi-levered landing gear for an aircraft includes a main shock absorber strut, a bogie beam and an auxiliary actuator mechanism. The bogie beam extends fore and aft of an airframe of the aircraft with forward and aft axles for respective forward and aft wheels, and a main pivot between the forward and aft axle pivotally connected to the lower portion of the main shock absorber strut. The auxiliary actuator mechanism includes a spring unit pivotally connected at a lower end to an auxiliary pivot on the bogie forward of the main pivot, and at an upper end to an anchor point offset from the pivot connection of the upper portion to the aircraft fuselage. During stowing the strut and spring unit pivot together about different pivot points, causing a relative longitudinal movement between the main pivot and auxiliary pivot that further tilts the bogie beam to a stowing position.

    Abstract translation: 用于飞行器的半起落架起落架包括主减震器支柱，转向架梁和辅助致动器机构。 转向架梁用于相应的前轮和后轮的前轮和后轴的飞机机身的前后延伸，并且前后轴之间的主枢轴枢转地连接到主减震器支柱的下部。 辅助致动器机构包括弹簧单元，该弹簧单元在下端处枢转地连接到主枢轴前方的转向架上的辅助枢轴上，并且在上端处于从上部的枢转连接偏离飞行器机身的锚定点。 在收起期间，支柱和弹簧单元围绕不同的枢转点枢转在一起，导致主枢轴和辅助枢轴之间的相对纵向运动，其进一步将转向架梁倾斜到收起位置。

    Landing gear
    17.
    发明授权
    Landing gear 有权
    起落架

    公开(公告)号：US08376272B2

    公开(公告)日：2013-02-19

    申请号：US13333138

    申请日：2011-12-21

    Applicant: Ian Bennett ,  Richard Charles Lang ,  Robert Anthony Menezes

    Inventor： Ian Bennett ,  Richard Charles Lang ,  Robert Anthony Menezes

    IPC: B64C25/26 ,  B64C25/34 ,  B64C25/62

    CPC classification number: B64C25/60 ,  B64C25/22 ,  B64C25/34 ,  B64C25/58

    Abstract: An auxiliary actuator mechanism includes a lever, a spring unit and a control linkage. The lever is pivotally connected to the upper portion of a main shock absorber strut, and pivotable between an upper position for take-off, and a lower position. The spring unit is pivotally connected at an upper end to the lever and at a lower end to the bogie at an auxiliary pivot forward of the main pivot. The control linkage is connected between the lever and the upper portion of the main shock absorber strut to define the upper predetermined position of the lever. The control linkage is connectable to an anchor point that moves relative to the upper portion of the main shock absorber strut during stowing, and is operated by initial stowing movement of the stowing mechanism to lower the lever from the upper position to a stowing position.

    Abstract translation: 辅助致动器机构包括杆，弹簧单元和控制连杆。 杠杆枢转地连接到主减震器支柱的上部，并且可以在用于起飞的上部位置和下部位置之间枢转。 弹簧单元在上端枢转地连接到杠杆，并且在下端处以主枢轴前方的辅助枢轴枢转地连接到转向架。 控制联动装置连接在杠杆和主减震器支柱的上部之间，以限定杠杆的上部预定位置。 控制联动装置可连接到在收起期间相对于主减震器支柱的上部移动的锚点，并且通过收起机构的初始收起运动来操作以将杠杆从上部位置降低到收起位置。

    SPINAL IMPLANT AND METHOD FOR RESTRICTING SPINAL FLEXION
    19.
    发明申请
    SPINAL IMPLANT AND METHOD FOR RESTRICTING SPINAL FLEXION 有权
    脊柱植入物和限制脊柱弯曲的方法

    公开(公告)号：US20120123482A1

    公开(公告)日：2012-05-17

    申请号：US13340483

    申请日：2011-12-29

    Applicant: Louis Fielding ,  Ian Bennett ,  Colin Cahill ,  Pat Arensdorf ,  Ralph Crisostomo ,  Todd Alamin

    Inventor： Louis Fielding ,  Ian Bennett ,  Colin Cahill ,  Pat Arensdorf ,  Ralph Crisostomo ,  Todd Alamin

    IPC: A61B17/88

    CPC classification number: A61B17/7062

    Abstract: A spinal implant system for restricting flexion of a spine includes an elongate band proportioned to engage at least two spinous processes. During use, the band is positioned engaging the spinous processes at a spinal segment of interest, where it restricts flexion at the segment. The length and tension of the band may be adjustable following to implantation using percutaneous or transcutaneous means.

    Abstract translation: 用于限制脊柱弯曲的脊柱植入系统包括成比例的细长带以接合至少两个棘突。 在使用期间，带被定位成与感兴趣的脊髓部分处的棘突接合，其中它限制了该部分的屈曲。 在使用经皮或经皮手段进行植入之后，带的长度和张力可以是可调节的。

    Landing gear
    20.
    发明授权
    Landing gear 有权
    起落架

    公开(公告)号：US08104711B2

    公开(公告)日：2012-01-31

    申请号：US11997720

    申请日：2006-08-04

    Applicant: Ian Bennett ,  Richard C. Lang ,  Robert A. Menezes

    Inventor： Ian Bennett ,  Richard C. Lang ,  Robert A. Menezes

    IPC: B64C25/22 ,  B64C25/40 ,  B64C25/58

    CPC classification number: B64C25/60 ,  B64C25/22 ,  B64C25/34 ,  B64C25/58

    Abstract: An auxiliary actuator (49) comprises a two stage telescopic hydraulic unit comprising first (59, 63) and second (56, 50) stage piston and cylinder actuators operating coaxially within an outer casing (50). A respective actuator is connected to a respective one of the strut (1) and bogie beam (4). The second stage actuator (56, 60) serves to control the tilt position of the bogie beam (4) relative to the strut (1). The second stage actuator (56. 60), when in the retracted position with the first stage actuator (59, 63) in the extended position, limits the length ol the auxiliary actuator (9) between its connections (62,67) to the strut (1) and bogie beam (4), so as to assume a predetermined intermediate length in which the bogie beam (4) is restrained to tilt about the auxiliary pivot (14) and thereby lengthens the landing gear during take-off.

    Abstract translation: 辅助致动器（49）包括两级伸缩液压单元，其包括在外壳（50）内同轴运行的第一（59,63）和第二（56,50）级的活塞和气缸致动器。 相应的致动器连接到支柱（1）和转向架​​梁（4）中的相应的一个。 第二级致动器（56,60）用于控制转向架（4）相对于支柱（1）的倾斜位置。 当处于处于延伸位置的第一级致动器（59,63）的缩回位置时，第二级致动器（56.60）将辅助致动器（9）在其连接（62,67）之间的长度限制到 支柱（1）和转向架​​梁（4），以便呈现预定的中间长度，其中转向架梁（4）被限制在辅助枢轴（14）周围倾斜，从而在起飞期间延长起落架。

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