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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。

    Rocket cluster divert and attitude control system
    4.
    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
    5.
    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。