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    Damped split beam structural member with segmented beam parts
    5.
    发明授权
    Damped split beam structural member with segmented beam parts 有权
    带有分段梁部件的阻尼分束结构件

    公开(公告)号：US08757601B2

    公开(公告)日：2014-06-24

    申请号：US13227744

    申请日：2011-09-08

    申请人： David R. Sar ,  Terry M. Sanderson

    发明人： David R. Sar ,  Terry M. Sanderson

    IPC分类号： F16F7/08 ,  E04C2/34

    CPC分类号： B64C3/185 ,  F16F7/08 ,  F16F15/04

    摘要： A structural member includes a split beam within a box structure. The split beam may be a segmented beam that includes multiple segments for each of its parts. Movement of the split beam parts within the box structure, as the structural member flexes, dissipates energy and adds to the damping of the structural member.

    摘要翻译： 结构构件包括盒结构内的分束。 分割梁可以是分段梁，其包括用于其每个部分的多个段。 当结构构件弯曲时，箱结构内的分离梁部件的运动消耗能量并增加结构构件的阻尼。

    Aircraft wing with flexible skins
    6.
    发明授权
    Aircraft wing with flexible skins 有权
    飞机机翼具有柔软的外观

    公开(公告)号：US08714476B2

    公开(公告)日：2014-05-06

    申请号：US13278493

    申请日：2011-10-21

    申请人： Jack W. Reany ,  Terry M. Sanderson

    发明人： Jack W. Reany ,  Terry M. Sanderson

    IPC分类号： B64C3/38

    CPC分类号： B64C3/56 ,  B64C2201/102

    摘要： A wing includes a spar, and a pair of flexible skins that are attached to the spar. The spar is at the leading edge of the wing, and the skins extend toward the trailing edge of the wing. The wing deploys from a stowed condition, in which the skins are curved in the same direction around a fuselage of an aircraft, to a deployed condition, in which the skins provide the wing with an airfoil cross-sectional shape, for example with the skins curve in opposite direction. A lock is used to maintain the skins in the deployed state, with the lock for example located at the trailing edge of the wing. The lock may be a mechanical mechanism that automatically locks the wing in the deployed state, preventing the wing from returning to the stowed state.

    摘要翻译： 翼包括翼梁，以及一对连接到翼梁的柔性皮。 翼梁位于机翼的前缘，皮面朝向机翼的后缘延伸。 机翼从收起的状态部署，其中皮肤沿着飞机的机身在相同的方向上弯曲到部署状态，其中皮肤为翼提供翼型横截面形状，例如与皮肤 曲线相反。 使用锁来将皮肤保持在展开状态，例如锁定位于翼的后缘。 锁可以是机械机构，其将机翼自动地锁定在展开状态，防止机翼返回到收起状态。

    AIRCRAFT WING WITH KNUCKLED RIB STRUCTURE
    7.
    发明申请
    AIRCRAFT WING WITH KNUCKLED RIB STRUCTURE 有权
    飞机与KNUCKLED RIB结构

    公开(公告)号：US20130099050A1

    公开(公告)日：2013-04-25

    申请号：US13278477

    申请日：2011-10-21

    申请人： Terry M. Sanderson ,  Michael S. Cherry ,  Jack W. Reany

    发明人： Terry M. Sanderson ,  Michael S. Cherry ,  Jack W. Reany

    IPC分类号： B64C3/56 ,  B64C3/38

    CPC分类号： B64C3/56 ,  B64C2201/102

    摘要： An aircraft wing has hinged ribs, and a skin covering the ribs. The ribs each include plural rib sections, array from the leading edge of the wing, to the trailing edge of the wing, and a lock to hold the rib sections together in a deployed state or condition. The wings are initially in a stowed state, with the ribs and the rib sections having a curved chord, and deploy to the deployed state, in which the ribs have a straightened chord that defines an airfoil state. The wing may have foam material between the ribs to allow the wings to expand in the wingspan direction, for instance after the ribs have been placed in the deployed state.

    摘要翻译： 飞机机翼有铰链肋骨和覆盖肋骨的皮肤。 肋条各自包括从翼的前缘到翼的后缘阵列的多个肋部，以及在展开状态或状态下将肋部保持在一起的锁。 翼部最初处于收起状态，肋和肋部具有弯曲的弦，并且部署到展开状态，其中肋具有限定翼型状态的拉直弦。 机翼可以在肋之间具有泡沫材料，以允许翼在翼展方向上膨胀，例如在肋已经处于展开状态之后。

    Structure with reconfigurable polymer material
    8.
    发明授权
    Structure with reconfigurable polymer material 有权
    具有可重构聚合物材料的结构

    公开(公告)号：US08382042B2

    公开(公告)日：2013-02-26

    申请号：US12120271

    申请日：2008-05-14

    申请人： Terry M. Sanderson ,  Yvonne C. Levenson ,  David R. Sar

    发明人： Terry M. Sanderson ,  Yvonne C. Levenson ,  David R. Sar

    IPC分类号： B64C9/00

    CPC分类号： B29C44/56 ,  B29C61/00 ,  B29L2031/30 ,  Y10T428/249953 ,  Y10T428/249995

    摘要： A structure includes a polymer structural member, which may include a shape memory polymer material, that can change its size and/or shape. An electromagnetic source is used to impose an electric field or a magnetic field on the polymer structural material, in order to control the shape of the material. The force may be used to change the shape of the material and/or to maintain the shape of the material while it is under load. The polymer material may be a solid material, may be a foam, and/or may include a gel. A shape memory polymer material may have mixed in it particles that are acted upon by the electromagnetic field. The structure may be used in any of a variety of devices where shape change (morphing), especially under loading, is desired.

    摘要翻译： 结构包括聚合物结构构件，其可以包括可改变其尺寸和/或形状的形状记忆聚合物材料。 电磁源用于在聚合物结构材料上施加电场或磁场，以便控制材料的形状。 该力可以用于改变材料的形状和/或在材料负载时保持材料的形状。 聚合物材料可以是固体材料，可以是泡沫，和/或可以包括凝胶。 形状记忆聚合物材料可以在其中混合被电磁场作用的颗粒。 该结构可以用于需要形状变化（变形），特别是在加载下的各种装置中的任何一种。

    INTERCEPTOR VEHICLE WITH EXTENDIBLE ARMS
    9.
    发明申请
    INTERCEPTOR VEHICLE WITH EXTENDIBLE ARMS 有权
    具有可扩展性的障碍物车辆

    公开(公告)号：US20120180691A1

    公开(公告)日：2012-07-19

    申请号：US12327981

    申请日：2008-12-04

    申请人： David R. Sar ,  Terry M. Sanderson ,  Philip C. Theriault

    发明人： David R. Sar ,  Terry M. Sanderson ,  Philip C. Theriault

    IPC分类号： F42B12/02 ,  F42B12/72

    CPC分类号： F42B12/34

    摘要： A kinetic anti-projectile vehicle includes a body, and extendible arms that extend radially from the body. The arms include a foam material, such as a shape memory foam. The foam material may be heated to expand it. The foam arms may be mechanically restrained while being heated. The mechanically restraint may be removed by heating, for example including a fusible link or a shape memory sold material. The foam material arms may include solid material, either in the form of solid material particles, such as high strength particles, or in the form of supports or restraints in the foam material. The extension of the foam arms increases the effective area of the vehicle for impacting a projectile. Impact on the projectile from the body and/or one or more of the arms may be sufficient to destroy, divert, or otherwise disable the projectile.

    摘要翻译： 动力学防弹丸车辆包括主体和从身体径向延伸的可延伸臂。 臂包括泡沫材料，例如形状记忆泡沫。 泡沫材料可以被加热以使其膨胀。 泡沫臂可以在加热时被机械地约束。 机械约束可以通过加热来移除，例如包括可熔连接件或形状记忆销售材料。 泡沫材料臂可以包括固体材料，其以固体材料颗粒的形式，例如高强度颗粒，或泡沫材料中的支撑体或约束形式。 泡沫臂的延伸增加了用于撞击弹丸的车辆的有效面积。 从身体和/或一个或多个武器对射弹的影响可能足以摧毁，转移或以其他方式使射弹失效。

    Collapsible shape memory alloy (SMA) nose cones for air vehicles, method of manufacture and use
    10.
    发明授权
    Collapsible shape memory alloy (SMA) nose cones for air vehicles, method of manufacture and use 有权
    用于空中客车的可折叠形状记忆合金（SMA）鼻锥，制造和使用方法

    公开(公告)号：US08058595B2

    公开(公告)日：2011-11-15

    申请号：US12141426

    申请日：2008-06-18

    申请人： Frederick B. Koehler ,  Ward D. Lyman ,  Terry M. Sanderson

    发明人： Frederick B. Koehler ,  Ward D. Lyman ,  Terry M. Sanderson

    IPC分类号： B64C7/00

    CPC分类号： B64C1/36 ,  F42B10/46 ,  F42B12/76 ,  Y10T29/49865

    摘要： A nose cone formed from a shape memory alloy (SMA) having a recoverable strain of at least 2% collapses about the dome for storage, deploys at launch to protect the sensor dome and reduce drag during atmospheric flight and is shed to allow sensing for terminal maneuvers. The SMA is shape-set at elevated temperatures in its Austenite phase with a memorized shape having a radius of curvature greater than that of the sensor dome to reduce aerodynamic drag. The temperature is reduced and the SMA collapsed to conform to the curvature of the sensor dome within the recoverable strain for storage. A first mechanism is configured to return the collapsed SMA to its memorized shape at launch or prior to going supersonic. In one embodiment, the SMA is stored below its Martensite finish temperature in a temperature-induced Martensite phase in which case the mechanism heats the SMA above the Austenite finish temperature to return the material to its memorized shape. In another embodiment, the SMA is stored above its Austenite finish temperature in which case collapsing the SMA places the material in a strain-induced Martensite phase. The mechanism holds the collapsed SMA in place and the releases the stored energy allowing the SMA to return to the memorized shape.

    摘要翻译： 由具有至少2％的可恢复应变的形状记忆合金（SMA）形成的鼻锥在穹顶周围塌陷以进行存储，在发射时展开以保护传感器圆顶并在大气飞行期间减小阻力并被释放以允许感测终端 机动 SMA在其奥氏体相中的高温下成形，具有比传感器圆顶的曲率半径大的记忆形状，以减少气动阻力。 温度降低，并且SMA收缩以符合传感器圆顶在可恢复应变中的曲率以进行存储。 第一机构被配置为在发射或超音速之前将折叠的SMA返回到其记忆形状。 在一个实施例中，SMA在温度诱导的马氏体相中存储在其马氏体终止温度之下，在这种情况下，机构将SMA加热到高于奥氏体终点温度以将材料返回到其记忆形状。 在另一个实施方案中，SMA被存储在其奥氏体终点温度之上，在这种情况下，SMA将材料放置在应变诱发的马氏体相中。 该机构将折叠的SMA保持在适当的位置，释放存储的能量，使SMA能够返回到记忆形状。