公开(公告)号：US20100116937A1

公开(公告)日：2010-05-13

申请号：US12616812

申请日：2009-11-12

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

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

IPC分类号： B64C3/00 ,  B64C3/18 ,  E04H12/18

CPC分类号： B64C3/185 ,  B64C3/48 ,  B64C3/56 ,  B64C2201/102

摘要： A wing, such as a wing for an unmanned aerial vehicle (UAV), includes a beam or box that can be selectively expanded from a collapsed condition, to increase the thickness of the wing. The beam may include a pair of plates that are close together when the beam is in a collapsed condition, and separate from one another to put the beam in an expanded condition. The plates may be substantially parallel to each other, and may have shape memory foam and/or resilient devices, such as coil springs, between them, in order to provide a force to separate the plates before, during, and/or after deployment of the wing. The expandable/collapsible beam may have a lock mechanism to lock it into place when the beam is in an expanded condition.

摘要翻译： 诸如用于无人驾驶飞行器（UAV）的机翼的机翼包括可以从折叠状态选择性地扩展的梁或箱，以增加机翼的厚度。 梁可以包括一对板，当梁处于折叠状态时，彼此分离并将梁放置在膨胀状态下，它们靠近在一起。 板可以基本上彼此平行，并且在它们之间可以具有形状记忆泡沫和/或弹性装置，例如螺旋弹簧，以便在部署之前，期间和/或之后提供力分离板 机翼。 可膨胀/可折叠的梁可以具有锁定机构，以在梁处于膨胀状态时将其锁定到位。

公开(公告)号：US20080309195A1

公开(公告)日：2008-12-18

申请号：US12185246

申请日：2008-08-04

申请人： Terry M. Sanderson

发明人： Terry M. Sanderson

IPC分类号： G01P15/09

CPC分类号： G01N29/12 ,  G01M5/0041 ,  G01M5/0066 ,  G01N29/2475 ,  G01N2291/0231 ,  G01N2291/0232 ,  G01N2291/0235 ,  G01N2291/0258 ,  G01N2291/02827 ,  G01P15/0885 ,  G01P15/09

摘要： Piezomagnetic, magneto-strictive, or electro-strictive material particles may also be distributed throughout the structural material of the structural member, which serve to amplify and otherwise enhance the signals from the piezoelectric material particles. The piezoelectric, electro-strictive, magneto-strictive, and/or piezomagnetic material particles may allow the structural member to exhibit an electrical and/or magnetic response to forces on the structural member, such as accelerations. This may allow the structural member to function as a force sensor or an accelerometer. Signals induced by such external forces or accelerations may be taken from the conductive pickups and used for various operations, for example, for arming a warhead of a missile or for triggering passenger safety features such as air bags in automobiles.

摘要翻译： 压电，磁致密或电严格材料颗粒也可以分布在结构构件的整个结构材料中，其用于放大或以其它方式增强来自压电材料颗粒的信号。 压电，电严格，磁致密和/或压电材料颗粒可以允许结构构件对结构构件上的力（例如加速度）呈现电和/或磁响应。 这可以允许结构构件用作力传感器或加速度计。 由这种外力或加速度引起的信号可以从导电拾音器获取并用于各种操作，例如用于布置导弹的弹头或用于触发乘客安全特征，例如汽车中的气囊。

公开(公告)号：US06242717B1

公开(公告)日：2001-06-05

申请号：US09385804

申请日：1999-08-30

申请人： Terry M. Sanderson

发明人： Terry M. Sanderson

IPC分类号： F27B936

CPC分类号： F26B13/002 ,  C03C25/12 ,  F26B3/28 ,  H05B3/0038

摘要： A removable rack for supporting a reflector in an oven having a light source where the reflector focuses light emitted from the light source in a predetermined manner. The preferred removable rack is arranged and configured to support a mirror array therein where the entire rack can be removably fixed to the interior of the oven in which it will be used. The rack is preferably arranged and configured to releasably engage the mirror array therein. A method for replacing a reflector disposed in the internal portion of an oven having a light source comprising the steps of providing a removable support rack for releasably supporting the reflector removably fixed to an interior portion of an oven. A reflector can be replaced by removing a member, fixing the removable support rack to the interior portion of the oven and removing the removable support rack from the interior of the oven. The rack and the mirror arrays supported thereon can be removed from the oven collectively by disengaging fixing members fixing the rack to the oven interior. The mirrors can then be removed from the rack by disengaging a support portion of the rack, thereby releasing the mirrors.

摘要翻译： 一种用于在具有光源的烘箱中支撑反射器的可移除的支架，其中反射器以预定的方式聚焦从光源发出的光。 优选的可拆卸机架被布置和配置为支撑其中的整个机架可拆卸地固定在其将被使用的烤箱内部的反射镜阵列。 齿条优选地被布置和构造成可释放地接合其中的反射镜阵列。 一种用于更换布置在具有光源的烘箱的内部的反射器的方法，包括以下步骤：提供可移除的支撑架，用于可拆卸地支撑反射器，其可移除地固定到烤箱的内部。 可以通过去除构件来代替反射器，将可移除的支撑架固定到烤箱的内部，并从烤箱的内部移除可移除的支撑架。 支撑在其上的支架和反射镜阵列可以通过将固定支架的固定构件脱离到烤箱内部而集中地从烤箱中移除。 然后可以通过使机架的支撑部分脱离从而将镜子从架子上移除，从而释放反射镜。

公开(公告)号：US08324563B2

公开(公告)日：2012-12-04

申请号：US12752221

申请日：2010-04-01

申请人： Michael J. Broyles ,  Terry M. Sanderson ,  Douglas M. Beard ,  Brian D. Alfing

发明人： Michael J. Broyles ,  Terry M. Sanderson ,  Douglas M. Beard ,  Brian D. Alfing

IPC分类号： H01J5/02

CPC分类号： F16J13/18 ,  F16J13/02 ,  F16J15/128

摘要： A container includes a housing and a cover which may be wholly or partially removed to open the container. A foil seal is used to seal the joint between the housing and the cover. The foil seal is internal to the container. The foil seal separates during opening of the cover, respective parts of the foil seal remaining with the housing and the cover. The foil seal may be a metal or metal-containing foil, for example being an aluminum, steel, or titanium foil, or a metalized plastic foil. A cutter, such as a serrated edge, may be positioned to facilitate cutting of the foil seal during cover opening. The container may be part of a seeker assembly with the housing being a seeker housing, and the cover being a removable or hinged cover that protects an optical seeker during some portions of flight, such as during launch of a spacecraft.

摘要翻译： 容器包括壳体和可以完全或部分地移除以打开容器的盖子。 箔密封用于密封外壳和盖子之间的接头。 箔密封件在容器内部。 箔盖在打开盖子期间分开，箔封口的相应部分保留在外壳和盖子上。 箔密封件可以是金属或含金属箔，例如铝，钢或钛箔，或金属化塑料箔。 诸如锯齿状边缘的切割器可以被定位成便于在盖打开期间切割箔密封件。 容器可以是引导器组件的一部分，其中壳体是引导器壳体，并且盖是可移除或铰接的盖，其在飞行的某些部分（例如在发射航天器期间）保护光学探测器。

公开(公告)号：US08016249B2

公开(公告)日：2011-09-13

申请号：US12120273

申请日：2008-05-14

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

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

IPC分类号： B64C3/54

CPC分类号： B64C3/54 ,  B29C61/00 ,  B29L2031/3085 ,  F01D5/14 ,  F01D5/28 ,  F05B2240/31 ,  F05D2250/70 ,  Y02T50/14 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T428/12333

摘要： A shape-changing structural member has a shape-changing material, such as a suitable foam material, for example a polymer foam capable of withstanding at least 300% strain or a metal alloy foam capable of withstanding at least 5% strain. Springs, such as one or more coil springs, provide structural support for the shape-changing material. The springs may also be used to provide forces to expand and contract the shape change material. The springs may include pairs of concentric springs, one inside of another. The concentric springs may surround an underlying skeleton structure that supports the shape-changing material and/or aids in changing the shape of the material. The concentric springs may or may not be wrapped around the underlying skeleton structure. Multiple springs or pairs of springs may be coupled together using a sheet metal connector.

摘要翻译： 形状改变的结构构件具有形状改变材料，例如合适的泡沫材料，例如能够承受至少300％应变的聚合物泡沫或能够承受至少5％应变的金属合金泡沫。 诸如一个或多个螺旋弹簧的弹簧为形状改变材料提供结构支撑。 这些弹簧也可以用于提供力以使形状变化材料膨胀和收缩。 弹簧可以包括成对的同心弹簧，一个在另一个的内部。 同心弹簧可以围绕支撑形状改变材料的底层骨架结构和/或有助于改变材料的形状。 同心弹簧可以或可以不包裹在下面的骨架结构周围。 多个弹簧或弹簧对可以使用钣金连接器联接在一起。

公开(公告)号：US08007705B2

公开(公告)日：2011-08-30

申请号：US12404283

申请日：2009-03-14

申请人： Terry M. Sanderson

发明人： Terry M. Sanderson

IPC分类号： B28B7/30

CPC分类号： B29C33/505 ,  B29C70/30 ,  B29L2031/3085 ,  B33Y30/00 ,  B33Y70/00

摘要： A polymer is formed into the shape of a one-piece composite part and then solidified by curing, setting, hardening or otherwise solidifying the polymer to form a shaped polymer form having a shape that does not draw. Composite material is laid up on the form and solidified to from the composite part. The rigidity required of the form to lay up the composite part can he provided by operating in the polymer form's glassy state, forming the shaped polymer form with a hollow core and placing a rigid insert designed to draw inside the hollow core with the polymer form in its elastomeric state or through a combination of both. In its elastomeric state the form becomes pliable (without relaxing to a different memorized shape) and can he drawn out of the one-piece composite part. Because the shape of the form does not draw, the form deforms as it is drawn. If used, the rigid insert is drawn out prior to removing the shaped polymer form. Upon removal, the polymer form in its elastomeric state returns to its original shape. The form may be used once and thrown away or reused to form multiple composite parts of the same shape.

摘要翻译： 将聚合物形成为单件复合部件的形状，然后通过固化，固化，硬化或以其它方式固化聚合物固化，形成具有不拉伸形状的成型聚合物形式。 将复合材料放置在复合材料的表面上并固化。 可以通过以聚合物形式的玻璃状态操作来提供形成复合部件的刚性所需的刚性，用中空芯形成成形聚合物形式，并且放置刚性插入物，该刚性插入物被设计成以聚合物形式在中空芯内部 其弹性状态或两者的组合。 在其弹性状态下，该形状变得柔软（不放松到不同的记忆形状），并且可以从单件复合部件中拉出。 由于形状的形状没有绘制，所以形状随着拉伸而变形。 如果使用，刚性插入物在除去成形聚合物形式之前被拉出。 去除时，其弹性体状态的聚合物形状恢复到其初始形状。 该形式可以使用一次并且丢弃或重新使用以形成相同形状的多个复合部件。

公开(公告)号：US20100282906A1

公开(公告)日：2010-11-11

申请号：US12463400

申请日：2009-05-10

申请人： Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

发明人： Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

IPC分类号： B64C3/00 ,  B64C1/00

CPC分类号： B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  F42B10/14 ,  F42B10/146 ,  F42B10/16 ,  F42B10/20

摘要： A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

摘要翻译： 层压翼结构包括至少一层金属材料和至少一层形状记忆聚合物（SMP）材料。 将SMP加热到其玻璃化转变带Tg的温度，以将机身周围的机翼卷绕成储存位置。 金属层必须足够薄以便在卷起时保持低于其屈服点。 在准备发射时，SMP材料被热激活，允许存储在金属材料层中的应变能在发射时将机翼返回到其展开位置。 一旦部署，SMP冷却到玻璃状态。 SMP材料可以用纤维增强以形成聚合物基质复合材料（PMC）。 SMP可用于为多个金属层提供剪切应变消除。 通过卸载将机翼从SMP返回到金属的原始展开位置所需的动力，聚合物不会获得永久变形，并且可以准确地展开机翼。

公开(公告)号：US07694578B2

公开(公告)日：2010-04-13

申请号：US11936247

申请日：2007-11-07

申请人： David B. Hatfield ,  Terry M. Sanderson ,  Renee M. Rodgers

发明人： David B. Hatfield ,  Terry M. Sanderson ,  Renee M. Rodgers

IPC分类号： G01D1/16

CPC分类号： G01N3/20 ,  G01B5/213 ,  G01B5/30 ,  G01B11/16 ,  G01B11/255

摘要： A method of evaluating material properties of polymeric materials includes making one or more material samples or slabs, with each of the samples or slabs having a pair of material layers in contact with one another. The layers are layers of organic matrix polymer material that have different characteristics from each other, for example having a difference in composition and/or cure characteristics. Characteristics of the test slabs and the interface between the layers can be determined by examining curvatures of the test slabs. A number of samples may be made up having the same material in a first layer, and range of different materials in the respective second layers. The range may cover a range of various material compositions and/or cure characteristics.

摘要翻译： 评估聚合材料的材料性质的方法包括制备一种或多种材料样品或板坯，其中每个样品或板坯具有彼此接触的一对材料层。 这些层是具有彼此不同特征的有机基质聚合物材料层，例如具有组成和/或固化特性的差异。 测试板的特性以及层之间的界面可以通过检查测试板的曲率来确定。 可以在第一层中制备具有相同材料的多个样品，以及各个第二层中不同材料的范围。 该范围可以涵盖各种材料组成和/或固化特性的范围。

公开(公告)号：US20090314890A1

公开(公告)日：2009-12-24

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 ,  B23P11/02

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。

公开(公告)号：US20090286101A1

公开(公告)日：2009-11-19

申请号：US12120275

申请日：2008-05-14

申请人： David R. Sar ,  Terry M. Sanderson ,  Thomas P. McCreery

发明人： David R. Sar ,  Terry M. Sanderson ,  Thomas P. McCreery

IPC分类号： B32B5/18

CPC分类号： B64C3/54 ,  B64C3/40 ,  B64C5/02 ,  B64C5/18 ,  C22F1/006 ,  C22F1/10 ,  Y02T50/14 ,  Y10T428/12326 ,  Y10T428/12479

摘要： A shape-changing structure has a superelastic metal foam structural member that changes shape (morphs) to change configuration of the structure. The superelastic metal foam structural member changes shape while maintaining a continuous outer surface, with the continuous metal foam material inside the outer surface expanding, contracting, or otherwise changing shape. The superelastic metal foam material may be heated above a transition temperature to allow it to change shape, and then cooled to cause it to increase in strength, more easily maintaining its new shape. The superelastic metal foam material may be a suitable alloy, for example a nickel titanium alloy, that exhibits superelastic (pseudoelastic) behavior. The superelastic metal foam material may be a shape memory alloy material that returns to a set shape upon moderate heating. The superelastic metal elastic foam structural member may be heated either by an internal heat source or by external heating.

摘要翻译： 变形结构具有改变形状（变形）以改变结构构型的超弹性金属泡沫结构构件。 超弹性金属泡沫结构构件在保持连续的外表面的同时改变形状，其中外表面内的连续金属泡沫材料膨胀，收缩或以其它方式改变形状。 超弹性金属泡沫材料可以在转变温度以上加热，以使其形状变化，然后冷却以使其增加强度，更容易保持其新形状。 超弹性金属泡沫材料可以是显示超弹性（假弹性）行为的合适的合金，例如镍钛合金。 超弹性金属泡沫材料可以是形状记忆合金材料，其在适度加热时恢复到固定形状。 超弹性金属弹性泡沫结构件可以通过内部热源或外部加热来加热。