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    SHAPE MEMORY ALLOY DISC VENT COVER RELEASE
    1.
    发明申请
    SHAPE MEMORY ALLOY DISC VENT COVER RELEASE 审中-公开
    形状记忆合金光盘盖发布

    公开(公告)号：WO2016167864A1

    公开(公告)日：2016-10-20

    申请号：PCT/US2016/017682

    申请日：2016-02-12

    Applicant: RAYTHEON COMPANY

    Inventor： LYMAN, Ward D. ,  KOEHLER, Frederick B.

    IPC: F42B39/20

    CPC classification number: F42B39/14 ,  F42B39/20

    Abstract: A release mechanism (108, 109, 111) includes a frame (204, 308, 502, 703) with an interior (503). The release mechanism also includes a prestrained shape memory alloy element (202, 306, 410, 506, 702, 802, 806) coupled to the interior of the frame. The prestrained element creates a seal with the frame. The prestrained element is notched in one or more regions and is configured to fracture in the notched regions when heated to a predetermined temperature allowing the interior to open. The remaining regions of the prestrained element are unfractured.

    Abstract translation: 释放机构（108,109,111）包括具有内部（503）的框架（204,308,502,703）。 释放机构还包括耦合到框架内部的预应变形状记忆合金元件（202,306,410,506,702,802,806）。 预制元件与框架形成密封。 预应变元件在一个或多个区域中被切口，并且被构造成在被加热到允许内部打开的预定温度时在凹口区域中断裂。 预应力元素的剩余区域是未受损的。

    THRUSTER WITH SEGMENTED PROPELLANT
    2.
    发明申请
    THRUSTER WITH SEGMENTED PROPELLANT 审中-公开
    推进器与分段推进剂

    公开(公告)号：WO2017176311A1

    公开(公告)日：2017-10-12

    申请号：PCT/US2016/056387

    申请日：2016-10-11

    Applicant: RAYTHEON COMPANY

    Inventor： KOEHLER, Frederick B. ,  DANFORTH, Jeremy C. ,  LYMAN, Ward D. ,  LANGHENRY, Mark T. ,  SUMMERS, Matt H. ,  PONTIUS, Paul E. ,  PAPE, Brian M. ,  STALLINGS, Jared D. ,  VILLARREAL, James K. ,  VILLARREAL, Thomas

    IPC: F02K9/26 ,  F02K9/32 ,  F02K9/94 ,  F02K9/95

    Abstract: A thruster includes multiple segments of electrically-operated propellant, electrodes for igniting one or a few of the electrically-operated propellant segments at a time, and a propellant feeder for moving further propellant segments into engagement with the electrodes. The segments may be configured to provide equal increments of thrust, or different amounts of thrust. The segments may each include an electrically-operated propellant material surrounded by a sealing material, so as to keep the propellant material away from moisture and other contaminants (and/or the vacuum of space) before each individual segment is to be used. The thruster may be included in any of a variety of flight vehicles, for example in a small satellite such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

    Abstract translation: 推进器包括多个电动推进剂段，用于一次点燃一个或几个电动推进剂段的电极，以及推进剂供给器，用于将另外的推进剂段移动到与 电极。 这些段可以被配置成提供相等的推力增量或不同的推力量。 这些区段可以各自包括由密封材料围绕的电操作推进剂材料，以便在每个单独的区段将被使用之前使推进剂材料远离湿气和其他污染物（和/或空间的真空）。 推进器可以包括在各种飞行器中的任何一种中，例如在诸如CubeSat卫星的小卫星中，例如具有大约1升的体积和不大于大约1.33kg的质量。

    TRIGGERING DEVICE WITH SAFETY VALVE AND LINKAGE
    3.
    发明申请
    TRIGGERING DEVICE WITH SAFETY VALVE AND LINKAGE 审中-公开

    公开(公告)号：WO2021062114A1

    公开(公告)日：2021-04-01

    申请号：PCT/US2020/052663

    申请日：2020-09-25

    Applicant: RAYTHEON COMPANY

    Inventor： KOEHLER, Frederick B. ,  LEE, Anthony O. ,  MEREMS, Paul A.

    IPC: F42C15/34 ,  F42B39/20 ,  F42C15/24

    Abstract: A heat-activated triggering device, such as for a missile or munition, includes a firing pin that is driven into a primer, to initiate a detonation and/or combustion reaction. The firing pin may be mechanically coupled to a linkage that prevents egress of output from the primer if the firing pin has not been moved. The linkage may include, for example, a cylindrical valve element with a through hole, the through hole being alignable with an output channel from the primer when the firing pin has been moved sufficiently. The movement of the firing pin slides a dowel pin that is attached to the firing pin. This in turn translates a cam element that turns the cylindrical element. Partial movement of the firing pin still may leave the valve closed. Preventing the primer from prematurely operating to trigger explosion, for example preventing full operation due to a primer being heated.

    HEAT-ACTIVATED TRIGGERING DEVICE WITH BI-METAL TRIGGERING ELEMENT
    6.
    发明申请
    HEAT-ACTIVATED TRIGGERING DEVICE WITH BI-METAL TRIGGERING ELEMENT 审中-公开

    公开(公告)号：WO2021061286A1

    公开(公告)日：2021-04-01

    申请号：PCT/US2020/045114

    申请日：2020-08-06

    Applicant: RAYTHEON COMPANY

    Inventor： KOEHLER, Frederick B. ,  LYMAN, Ward D. ,  LEE, Anthony O. ,  MEREMS, Paul A.

    IPC: F42B39/14 ,  F42B39/20 ,  F42C15/36 ,  F42C15/44

    Abstract: A heat-activated triggering device, such as for a missile or munition, includes a bi-metal trigger element, with a breakable pin of a first metal surrounded by a sleeve made of a second metal that is different than the first metal. The sleeve may be made of a shape memory alloy, such as a single-crystal shape memory alloy, that is pre-compresses around part of the pin. The sleeve may be configured to put a tension force on the pin as the sleeve passes a predetermined temperature, for instance a temperature at which the shape memory feature of the sleeve is activated. The pin may have a weakened portion, such as a notched portion, at which the pin breaks. The breaking of the pin may be used to drive a firing pin into a primer, to initiate a detonation and/or combustion reaction.

    CHORD-EXPANDING AIR VEHICLE WINGS
    7.
    发明申请
    CHORD-EXPANDING AIR VEHICLE WINGS 审中-公开
    扩展空中的车翼

    公开(公告)号：WO2013066439A1

    公开(公告)日：2013-05-10

    申请号：PCT/US2012/047834

    申请日：2012-07-23

    Applicant: RAYTHEON COMPANY ,  KOEHLER, Frederick B. ,  SANDERSON, Terry M. ,  REANY, Jack W.

    Inventor： KOEHLER, Frederick B. ,  SANDERSON, Terry M. ,  REANY, Jack W.

    IPC: B64C3/54 ,  B64C3/56 ,  F42B10/14

    CPC classification number: B64C3/56 ,  F42B10/14

    Abstract: An air vehicle wing includes foldable ribs (52) coupled to a leading-edge spar (32). The ribs each have multiple rib segments (52a-52d) which are foldable (hinged) relative to each other. Extension linkages (54), 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 (80) 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: 机动车翼包括联接到前缘翼梁（32）的可折叠肋（52）。 这些肋各自具有相对于彼此可折叠（铰接）的多个肋段（52a-52d）。 每个具有多个延伸链节段的延伸连杆（54）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，能够改变单个肋部分和延伸连接部分之间的相对角度， 它们是耦合的。 皮肤（80）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。

    VARIABLE BURN-RATE SOLID ROCKET MOTOR IGNITION METHOD
    8.
    发明申请
    VARIABLE BURN-RATE SOLID ROCKET MOTOR IGNITION METHOD 审中-公开

    公开(公告)号：WO2022055545A1

    公开(公告)日：2022-03-17

    申请号：PCT/US2021/016718

    申请日：2021-02-05

    Applicant: RAYTHEON COMPANY

    Inventor： KOEHLER, Frederick B. ,  MEISNER, Mark J. ,  VOLLIN, Jeff L.

    IPC: F02K9/70 ,  F02K9/95 ,  F02K9/08 ,  F42C19/08 ,  F02K9/28

    Abstract: A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.

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