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    ROCKET CLUSTER DIVERT AND ATTITUDE CONTROL SYSTEM
    1.
    发明申请
    ROCKET CLUSTER DIVERT AND ATTITUDE CONTROL SYSTEM 有权
    ROCKET CLUSTER DIVERT和态度控制系统

    公开(公告)号：US20150300780A1

    公开(公告)日：2015-10-22

    申请号：US14258274

    申请日：2014-04-22

    申请人： Raytheon Company

    发明人： Andrew B. Facciano ,  William G. Graves ,  Michael A. Barker ,  Michael S. Alkema ,  Jeffrey S. Larson

    IPC分类号： F41G7/00 ,  F42B15/01

    CPC分类号： F42B15/01 ,  F42B10/661 ,  F42B10/663

    摘要： A flight vehicle includes a nose portion, a fuselage retaining structure aft of the nose portion, and an axial motor for expelling axial thrust along a longitudinal axis of the flight vehicle. Radial motors are coupled to the retaining structure and axisymmetrically arranged about the axial motor. Each radial motor is configured to expel radial thrust radially outwardly in respect to the flight vehicle. Roll thrusters are operatively coupled with the radial motors and coupled to the fuselage retaining structure. The roll thrusters are configured to provide a roll moment of the flight vehicle about a central longitudinal axis of the flight vehicle. Ejectors are operatively coupled to the radial motors, and a controller is operatively coupled to the radial motors and the ejectors. The controller is configured to selectively fire and selectively eject the radial motors to maintain relative centering of a center of gravity of the flight vehicle.

    摘要翻译： 飞行器车辆包括鼻部，机身保持结构在前部的后部，以及用于沿着飞行器车辆的纵向轴线排出轴向推力的轴向马达。 径向电动机联接到保持结构并围绕轴向电动机轴对称布置。 每个径向马达构造成相对于飞行器车辆径向向外排出径向推力。 滚动推进器可操作地与径向马达耦合并联接到机身保持结构。 滚动推进器被配置成围绕飞行器车辆的中心纵向轴线提供飞行车辆的滚动时刻。 喷射器可操作地联接到径向马达，并且控制器可操作地联接到径向马达和喷射器。 控制器被配置为选择性地起动并选择性地弹出径向马达以维持飞行器车辆的重心的相对定心。

    Separable physical coupler using piezoelectric forces for decoupling
    2.
    发明授权
    Separable physical coupler using piezoelectric forces for decoupling 有权

    公开(公告)号：US10816026B2

    公开(公告)日：2020-10-27

    申请号：US15672651

    申请日：2017-08-09

    申请人： Raytheon Company

    发明人： Christopher S. Nordahl ,  David G. Manzi ,  Linda A. Gee ,  Andrew B. Facciano

    IPC分类号： H01L41/09 ,  F16B31/00 ,  B64G1/64

    摘要： A coupler for separable physically coupling together a pair of objects includes two parts, on opposite sides of a boundary, that have different piezoelectric characteristics. When an electric field is applied to the coupler parts the piezoelectric forces induce a mechanical stress that separates the parts. The parts may be made of the same or a similar material, such as a suitable ceramic material, with the different piezoelectric characteristics produced by templating the parts with different domain orientations, from different seeds, for example using a three-dimensional manufacturing processes. The coupler may be used to allow shock-free (or reduced shock) separation of parts, such as separation of stages of vehicles such as flight vehicles.

    SPECIAL FORCES REPLENISHMENT VEHICLE
    3.
    发明申请
    SPECIAL FORCES REPLENISHMENT VEHICLE 审中-公开
    特种部队代理车辆

    公开(公告)号：US20150284080A1

    公开(公告)日：2015-10-08

    申请号：US14471129

    申请日：2014-08-28

    申请人： Raytheon Company

    发明人： Andrew B. Facciano ,  Cody D. Tretschok ,  Rodney H. Krebs ,  Patrick D. Kranking

    IPC分类号： B64D1/12 ,  B64C9/32

    CPC分类号： B64D1/12 ,  B64D1/14 ,  F42B10/56 ,  F42B10/64 ,  F42B12/58 ,  F42B15/01 ,  F42B25/00

    摘要： A replenishment vehicle, such as a special forces replenishment vehicle is configured for being carried by and released from an aircraft. The replenishment vehicle, also referred to as a payload container, includes a storage cavity for storing a payload for being delivered to a target area. The payload may include any suitable provisions, and preferably provisions that are non-explosive during landing of the payload container, such as supplies for troops/operatives in the field, self-deploying radar or other detection devices, etc. The payload container is lobbed from the aircraft, such that the payload container is released while the aircraft is proceeding at an upwards trajectory. The payload container may be guided towards the target area by a guide portion such as a fin, wing, sail, chute, etc. The payload container is configured to enable the payload to survive release of the payload container from the aircraft and a subsequent landing.

    摘要翻译： 补充车辆，例如特种部队补给车辆被配置为由飞机携带和释放。 补充车辆也称为有效载荷容器，包括用于存储用于传送到目标区域的有效载荷的存储腔。 有效载荷可以包括任何适当的规定，并且优选地在有效载荷容器着陆期间是非爆炸性的，例如在现场的部队/操作人员的供应物，自身部署的雷达或其他检测装置等。有效载荷容器是开放的 从而使得有效载荷容器在飞行器向上移动的同时被释放。 有效载荷容器可以通过诸如翅片，翼，帆，滑槽等的引导部分朝向目标区域被引导。有效载荷容器被配置为使得有效载荷能够从有效载荷从飞机释放并随后着陆 。

    Rocket cluster divert and attitude control system
    5.
    发明授权
    Rocket cluster divert and attitude control system 有权
    火箭群转移和姿态控制系统

    公开(公告)号：US09377279B2

    公开(公告)日：2016-06-28

    申请号：US14258274

    申请日：2014-04-22

    申请人： Raytheon Company

    发明人： Andrew B. Facciano ,  William G. Graves ,  Michael A. Barker ,  Michael S. Alkema ,  Jeffrey S. Larson

    IPC分类号： F42B10/66 ,  F42B15/01 ,  F42B10/00 ,  F42B15/00

    CPC分类号： F42B15/01 ,  F42B10/661 ,  F42B10/663

    摘要： A flight vehicle includes a nose portion, a fuselage retaining structure aft of the nose portion, and an axial motor for expelling axial thrust along a longitudinal axis of the flight vehicle. Radial motors are coupled to the retaining structure and axisymmetrically arranged about the axial motor. Each radial motor is configured to expel radial thrust radially outwardly in respect to the flight vehicle. Roll thrusters are operatively coupled with the radial motors and coupled to the fuselage retaining structure. The roll thrusters are configured to provide a roll moment of the flight vehicle about a central longitudinal axis of the flight vehicle. Ejectors are operatively coupled to the radial motors, and a controller is operatively coupled to the radial motors and the ejectors. The controller is configured to selectively fire and selectively eject the radial motors to maintain relative centering of a center of gravity of the flight vehicle.

    摘要翻译： 飞行器车辆包括鼻部，机身保持结构在前部的后部，以及用于沿着飞行器车辆的纵向轴线排出轴向推力的轴向马达。 径向电动机联接到保持结构并围绕轴向电动机轴对称布置。 每个径向马达构造成相对于飞行器车辆径向向外排出径向推力。 滚动推进器可操作地与径向马达耦合并联接到机身保持结构。 滚动推进器被配置成围绕飞行器车辆的中心纵向轴线提供飞行车辆的滚动时刻。 喷射器可操作地联接到径向马达，并且控制器可操作地联接到径向马达和喷射器。 控制器被配置为选择性地起动并选择性地弹出径向马达以维持飞行器车辆的重心的相对定心。

    ROCKET PROPELLED PAYLOAD WITH DIVERT CONTROL SYSTEM WITHIN NOSE CONE
    6.
    发明申请
    ROCKET PROPELLED PAYLOAD WITH DIVERT CONTROL SYSTEM WITHIN NOSE CONE 有权
    带诺斯锥内的DIVERT控制系统的ROCKET PROPLEED PAYLOAD

    公开(公告)号：US20140138475A1

    公开(公告)日：2014-05-22

    申请号：US13669935

    申请日：2012-11-06

    申请人： Raytheon Company

    发明人： Andrew B. Facciano ,  Michael S. Alkema ,  Robert T. Moore

    IPC分类号： F41G7/00

    CPC分类号： F42B10/663

    摘要： A rocket is provided and includes booster stages at a rear of the nose cone, the booster stages being configured for propelling the nose cone in a propulsion direction and a divert control system housed entirely in the nose cone for controlling an orientation of the propulsion direction.

    摘要翻译： 提供火箭并且包括位于鼻锥后部的增压器级，助推器级构造成用于推动推进方向上的鼻锥，以及完全容纳在鼻锥中的转向控制系统，用于控制推进方向的取向。

    SEPARABLE PHYSICAL COUPLER USING PIEZOELECTRIC FORCES FOR DECOUPLING
    7.
    发明申请
    SEPARABLE PHYSICAL COUPLER USING PIEZOELECTRIC FORCES FOR DECOUPLING 审中-公开

    公开(公告)号：US20190048914A1

    公开(公告)日：2019-02-14

    申请号：US15672651

    申请日：2017-08-09

    申请人： Raytheon Company

    发明人： Christopher S. Nordahl ,  David G. Manzi ,  Linda A. Gee ,  Andrew B. Facciano

    IPC分类号： F16B31/00

    摘要： A coupler for separable physically coupling together a pair of objects includes two parts, on opposite sides of a boundary, that have different piezoelectric characteristics. When an electric field is applied to the coupler parts the piezoelectric forces induce a mechanical stress that separates the parts. The parts may be made of the same or a similar material, such as a suitable ceramic material, with the different piezoelectric characteristics produced by templating the parts with different domain orientations, from different seeds, for example using a three-dimensional manufacturing processes. The coupler may be used to allow shock-free (or reduced shock) separation of parts, such as separation of stages of vehicles such as flight vehicles.