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    Robotic grabber and method of use
    24.
    发明授权
    Robotic grabber and method of use 有权
    机器人抓取器和使用方法

    公开(公告)号：US08950795B2

    公开(公告)日：2015-02-10

    申请号：US13863634

    申请日：2013-04-16

    Applicant: Raytheon Company

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

    IPC: B66C1/44 ,  B25J15/00 ,  B25J15/12 ,  F03G7/06

    CPC classification number: F03G7/065 ,  B25J9/1085 ,  B25J15/12 ,  Y10S901/31

    Abstract: A robotic finger includes a shape-memory alloy and a shape-memory polymer connected to and adjacent to the shape-memory alloy. Heating the shape-memory polymer causes it to soften, heating the shape-memory alloy causes the alloy to bend in the direction of the shape-memory polymer to press the shape-memory polymer against an object to be grasped, and cooling the shape-memory polymer causes it to stiffen and to retain its shape. An opposing member is positioned to cooperate with the finger to grasp an object positioned between the finger and the opposing member. A selectively controllable heat source is capable of applying heat to the finger.

    Abstract translation: 机器人手指包括形状记忆合金和形状记忆合成物，该形状记忆合金与形状记忆合金连接并邻近形状记忆合金。 加热形状记忆聚合物使其软化，加热形状记忆合金导致合金在形状记忆聚合物的方向上弯曲以将形状记忆聚合物压靠待被抓握的物体， 记忆聚合物使其变硬并保持其形状。 相对的构件定位成与手指配合以抓住位于手指和相对构件之间的物体。 选择性控制的热源能够对手指施加热量。

    FRICTION DAMPING MECHANISM FOR DAMPED BEAMS AND OTHER STRUCTURES
    25.
    发明申请
    FRICTION DAMPING MECHANISM FOR DAMPED BEAMS AND OTHER STRUCTURES 有权
    阻尼梁和其他结构的摩擦阻尼机构

    公开(公告)号：US20140215936A1

    公开(公告)日：2014-08-07

    申请号：US13760665

    申请日：2013-02-06

    Applicant: RAYTHEON COMPANY

    Inventor： Terry M. Sanderson ,  Frederick B. Koehler ,  Thomas P. McCreery

    IPC: E04H9/02 ,  E04B1/98

    CPC classification number: E04H9/023 ,  E01D19/00 ,  E01D19/043 ,  E04B1/985 ,  E04H9/027 ,  F16F7/00 ,  F16F7/082 ,  F16F7/1022

    Abstract: A system includes a structure configured to undergo oscillatory movement. The system also includes a friction damping clamp coupled to the structure. The friction damping clamp includes a housing having a groove. The friction damping clamp also includes a roller positioned at least partially within the groove, where the groove has first and second ramps. The roller is configured to move up each ramp of the groove so that more compression is applied on the structure and to move down each ramp of the groove so that less compression is applied on the structure. The roller may be configured to apply more compression on the structure to increase friction between portions of the structure, to apply less compression on the structure to decrease friction between the portions of the structure, and to apply substantially no compression on the structure when the roller is located at a center of the groove.

    Abstract translation: 系统包括被配置为进行振荡运动的结构。 该系统还包括耦合到结构的摩擦阻尼夹具。 摩擦阻尼夹具包括具有凹槽的壳体。 摩擦阻尼夹具还包括至少部分地位于槽内的辊，其中槽具有第一和第二斜面。 辊被配置为向上移动槽的每个斜面，使得更多的压缩被施加在结构上并且向下移动槽的每个斜面，使得较少的压缩施加在结构上。 辊可以被配置为对结构施加更多的压缩以增加结构的部分之间的摩擦力，以减少结构上的压缩以减小结构部分之间的摩擦，并且当辊子基本上不施加压缩在结构上 位于凹槽的中心。

    CHORD-EXPANDING AIR VEHICLE WINGS
    26.
    发明申请
    CHORD-EXPANDING AIR VEHICLE WINGS 有权
    扩展空中的车翼

    公开(公告)号：US20130200208A1

    公开(公告)日：2013-08-08

    申请号：US13660209

    申请日：2012-10-25

    Applicant: Raytheon Company

    Inventor： Frederick B. Koehler ,  Terry M. Sanderson ,  Jack W. Reany

    IPC: B64C3/56

    CPC classification number: B64C3/56 ,  F42B10/14

    Abstract: An air vehicle wing includes foldable ribs coupled to a leading-edge spar. The ribs each have multiple rib segments which are foldable (hinged) relative to each other. Extension linkages, each with multiple extension linkage segments, pass through openings in the rib segments, and may be coupled to the rib segments with pin couplings, able to change relative angle between the individual rib segments and the extension linkage segments to which they are coupled. A skin may cover the ribs, to provide an outer surface of the wing that may be unfolded as the wing is expanded from a stowed, small-chord condition, to a deployed, large-chord condition.

    Abstract translation: 机动车翼包括连接到前缘翼梁的可折叠肋。 肋条各自具有相对于彼此可折叠（铰接）的多个肋段。 每个具有多个延伸链节段的延伸连接件穿过肋部段中的开口，并且可以通过销联接件联接到肋部分，能够改变各个肋部分与它们相连的延伸连接部分之间的相对角度 。 皮肤可以覆盖肋，以提供机翼的外表面，当机翼从收起的小弦条件扩展到展开的大和弦状态时，可以展开。

    MULTI-PULSE SOLID ROCKET MOTOR IGNITION METHOD
    27.
    发明申请
    MULTI-PULSE SOLID ROCKET MOTOR IGNITION METHOD 有权

    公开(公告)号：US20220170432A1

    公开(公告)日：2022-06-02

    申请号：US17106089

    申请日：2020-11-28

    Applicant: Raytheon Company

    Inventor： Frederick B. Koehler ,  Jacob A. Pinello-Benavides ,  Curtis S. Copeland ,  Isaiah M. McNeil ,  Paul Kadlec ,  Lauren E. Brunacini ,  Mark T. Langhenry

    IPC: F02K9/95 ,  F02K9/94 ,  F02K9/38

    Abstract: A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.

    Duct with shape memory material, and installation method
    28.
    发明授权
    Duct with shape memory material, and installation method 有权

    公开(公告)号：US10927987B2

    公开(公告)日：2021-02-23

    申请号：US14861043

    申请日：2015-09-22

    Applicant: Raytheon Company

    Inventor： Frederick B. Koehler ,  Ward D. Lyman ,  Delmar L. Barker ,  Teresa J. Clement

    IPC: F16L55/18 ,  F16L21/00 ,  B29C65/66 ,  F16L13/00 ,  B29C65/00 ,  B29C65/68

    Abstract: Ducting and/or duct couplings can be formed from shape memory polymer material, with the material for example being additively manufactured. The use of shape memory polymer material for one or more of the duct portions may allow for easier installation of the ducting, for example allowing the ducting to be warped and/or bent to fit into or through places that are hard to reach or hard to maneuver through, with the ducting then heated to cause it to return to a predetermined memory shape. The coupling of duct portions together may be accomplished by the duct portions including a shape memory polymer material, with for example ends of the duct portions fitted together, and then heated to use a shape memory property of the material to effect coupling. Heating of the shape memory polymer material also softens the material, allowing it to move to a previously set shape.

    Spacecraft with shape memory polymer deployment mechanism
    29.
    发明授权
    Spacecraft with shape memory polymer deployment mechanism 有权

    公开(公告)号：US10518908B2

    公开(公告)日：2019-12-31

    申请号：US14921545

    申请日：2015-10-23

    Applicant: Raytheon Company

    Inventor： Frederick B. Koehler ,  Ward D. Lyman ,  Matt H. Summers ,  Jeremy C. Danforth

    IPC: B64G1/22 ,  B64G1/10

    Abstract: A spacecraft, such as a satellite, uses a shape memory polymer actuator to deploy one or more deployable parts. The shape memory polymer actuator may be formed integrally with a deployable part and/or with a fuselage or other structure of the spacecraft, with the shape memory polymer actuator being for example a relatively thin portion of the shape memory polymer material of the integral structure. The shape memory actuator allows deployment of the deployable part(s) upon heating of the shape memory polymer material of the actuator, such as after the satellite has been launched into space. The heating may be caused by a heat source that is part of the spacecraft itself, or may be merely the result of exposing the spacecraft to solar heating after launch. The deployable part of the spacecraft may include any of a wide variety of parts that are used after launch.

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