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    Method of controlling missile flight using attitude control thrusters
    1.
    发明授权
    Method of controlling missile flight using attitude control thrusters 有权
    使用姿态控制推进器控制导弹飞行的方法

    公开(公告)号：US08058596B2

    公开(公告)日：2011-11-15

    申请号：US12548583

    申请日：2009-08-27

    Applicant: Lloyd E. Kinsey, Jr. ,  James M. Cook

    Inventor： Lloyd E. Kinsey, Jr. ,  James M. Cook

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

    CPC classification number: F42B10/661

    Abstract: A method of controlling flight of a missile includes using gyroscopes, such as pitch rate gyroscopes, to sense when a factor based on the angular rate of change of the missile exceeds a threshold value. One the threshold value is exceeded, a decision may be made to use one or more compensation thrusters to reduce the angular rate of change. The use of the compensation thrusters may correct residual angular velocities from a pitch over maneuver used to put the missile on an intended course. In addition, the compensation thrusters may be used to compensate for errors in missile heading induced after the pitch over maneuver, such as induced by misalignment of thrust provided by a main rocket motor of the missile. Multiple compensation thrusters may be used to compensate for angular changes in the pitch and yaw directions.

    Abstract translation: 控制导弹飞行的方法包括使用诸如俯仰速率陀螺仪的​​陀螺仪来感测何时基于导弹的角速度变化的因子超过阈值。 超过阈值的一个，可以决定使用一个或多个补偿推进器来减小角速度变化。 补偿推进器的使用可以校正用于将导弹放置在预期路线上的机动的俯仰的剩余角速度。 此外，补偿推进器可以用于补偿在机动之后引起的导弹航向的误差，例如由导弹的主火箭发动机提供的推力不对准引起的。 可以使用多个补偿推进器来补偿俯仰和偏航方向上的角度变化。

    METHOD OF CONTROLLING MISSILE FLIGHT USING ATTITUDE CONTROL THRUSTERS
    2.
    发明申请
    METHOD OF CONTROLLING MISSILE FLIGHT USING ATTITUDE CONTROL THRUSTERS 有权
    使用姿态控制雷达控制飞行器的方法

    公开(公告)号：US20110049289A1

    公开(公告)日：2011-03-03

    申请号：US12548583

    申请日：2009-08-27

    Applicant: Lloyd E. Kinsey, JR. ,  James M. Cook

    Inventor： Lloyd E. Kinsey, JR. ,  James M. Cook

    IPC: F42B10/66 ,  F42B15/01

    CPC classification number: F42B10/661

    Abstract: A method of controlling flight of a missile includes using gyroscopes, such as pitch rate gyroscopes, to sense when a factor based on the angular rate of change of the missile exceeds a threshold value. One the threshold value is exceeded, a decision may be made to use one or more compensation thrusters to reduce the angular rate of change. The use of the compensation thrusters may correct residual angular velocities from a pitch over maneuver used to put the missile on an intended course. In addition, the compensation thrusters may be used to compensate for errors in missile heading induced after the pitch over maneuver, such as induced by misalignment of thrust provided by a main rocket motor of the missile. Multiple compensation thrusters may be used to compensate for angular changes in the pitch and yaw directions.

    Abstract translation: 控制导弹飞行的方法包括使用诸如俯仰速率陀螺仪的​​陀螺仪来感测何时基于导弹的角速度变化的因子超过阈值。 超过阈值的一个，可以决定使用一个或多个补偿推进器来减小角速度变化。 补偿推进器的使用可以校正用于将导弹放置在预期路线上的机动的俯仰的剩余角速度。 此外，补偿推进器可以用于补偿在机动之后引起的导弹航向的误差，例如由导弹的主火箭发动机提供的推力不对准引起的。 可以使用多个补偿推进器来补偿俯仰和偏航方向上的角度变化。

    Method of intercepting incoming projectile
    3.
    发明授权
    Method of intercepting incoming projectile 有权
    拦截射弹的方法

    公开(公告)号：US08173946B1

    公开(公告)日：2012-05-08

    申请号：US12198146

    申请日：2008-08-26

    Applicant: William N. Patterson ,  James H. Dupont ,  Richard D. Loehr ,  Henri Y. Kim ,  Garrett L. Hall ,  James M. Cook

    Inventor： William N. Patterson ,  James H. Dupont ,  Richard D. Loehr ,  Henri Y. Kim ,  Garrett L. Hall ,  James M. Cook

    IPC: F41G7/00 ,  F42B15/01 ,  F42B15/00

    CPC classification number: F41H11/02 ,  F41F3/073 ,  F42B10/661 ,  F42B15/01 ,  F42B15/10

    Abstract: A method of defeating an incoming missile, such as a rocket propelled grenade, includes soft launching an interceptor missile, and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction. By launching at a relatively slow speed, such as a speed less than or equal to 40 m/sec (130 ft/sec), the interceptor missile may reach the desired interception direction within 250 milliseconds of launch. The interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location. For example, the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.

    Abstract translation: 一种击败诸如火箭推进手榴弹的进入导弹的方法包括软启动拦截导弹，然后使用拦截导弹发动机的俯仰角来将导弹的过程改变为所需的拦截方向。 通过以相对较慢的速度（例如小于或等于40米/秒（130英尺/秒）的速度）发射，拦截导弹可以在发射的250毫秒内达到所需的拦截方向。 拦截导弹可以能够围绕发射位置覆盖半球或更大程度上的所有拦截方向。 例如，拦截导弹可以从地面车辆垂直发射，并且能够在250毫秒内改变任何地面上的轨迹。

    System and method for attitude control of a flight vehicle using pitch-over thrusters and application to an active protection system
    4.
    发明授权
    System and method for attitude control of a flight vehicle using pitch-over thrusters and application to an active protection system 有权
    使用俯仰推进器的飞行器车辆姿态控制系统和方法以及应用于主动保护系统

    公开(公告)号：US07989743B2

    公开(公告)日：2011-08-02

    申请号：US12877789

    申请日：2010-09-08

    Applicant: Robert S. Brinkerhoff ,  Michael J. Mahnken ,  Richard D. Loehr ,  James M. Cook

    Inventor： Robert S. Brinkerhoff ,  Michael J. Mahnken ,  Richard D. Loehr ,  James M. Cook

    IPC: F42B15/01 ,  F42B10/00 ,  F42B15/00

    CPC classification number: F42B10/661 ,  G05D1/0883

    Abstract: A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability. Although this approach is applicable to provide attitude control for any flight vehicle including all types of missiles, kill-vehicles and space craft, it is particularly applicable for smaller highly maneuverable cost-constrained missile systems. One such system is an “Active Protection System” or APS in which a missile system is integrated with a vehicle such as a HumVee or armored personnel carrier to provide defensive counter-measures against possible attack.

    Abstract translation: 可靠和廉价的姿态控制系统使用多个俯仰推进器来为飞行器执行快速和精确的姿态操纵。 俯仰推进器产生直接俯仰和偏航飞行器的旋转力矩。 使用非常简单的推进器和控制技术提供了可靠且具有成本效益的解决方案。 使用单次固定脉冲推进器执行重叠俯仰和偏航操作的能力提供高速机动性。 虽然这种方法适用于为包括各种类型的导弹，杀伤车辆和航天飞机在内的任何飞行器提供姿态控制，但特别适用于较小的高度机动性的成本受限的导弹系统。 一个这样的系统是一个“主动保护系统”或APS，其中将导弹系统与诸如HumVee或装甲运兵车的车辆集成在一起，以提供防御性对策以防止可能的攻击。

    METHODS AND APPARATUS FOR INTERCEPTING A PROJECTILE
    7.
    发明申请
    METHODS AND APPARATUS FOR INTERCEPTING A PROJECTILE 有权
    拦截项目的方法和设备

    公开(公告)号：US20120211562A1

    公开(公告)日：2012-08-23

    申请号：US12134994

    申请日：2008-06-06

    Applicant: James M. Cook ,  Robert S. Brinkerhoff ,  Michael J. Mahnken

    Inventor： James M. Cook ,  Robert S. Brinkerhoff ,  Michael J. Mahnken

    IPC: G06G7/80

    CPC classification number: F41F3/055 ,  F41G7/007 ,  F41H11/02 ,  F42B15/04

    Abstract: Methods and apparatus for firing a projectile in response to a threat according to various aspects of the present invention operate in conjunction with a computer coupled to a launch system for the projectile. The computer may be configured to select the projectile from multiple available projectiles and calculate a fire control solution according to a characteristic of the selected projectile. Calculating the fire control solution may comprise deriving the fire control solution from a look-up table according to a predicted intercept point. The computer may initiate a launch of the selected projectile and provide the fire control solution to the selected projectile.

    Abstract translation: 根据本发明的各个方面的用于发射威胁的射弹的方法和装置与耦合到用于射弹的发射系统的计算机一起工作。 计算机可以被配置为从多个可用弹丸中选择弹丸，并根据所选弹丸的特征计算消防解决方案。 计算消防解决方案可以包括根据预测的拦截点从查找​​表导出火控解决方案。 计算机可以启动所选择的弹丸的发射，并向选定的弹丸提供消防控制解决方案。

    Electronic pneumatic brake system
    10.
    发明授权
    Electronic pneumatic brake system 失效
    电子气动制动系统

    公开(公告)号：US5924774A

    公开(公告)日：1999-07-20

    申请号：US712908

    申请日：1996-09-12

    Applicant: James M. Cook ,  Jeremy S. Waldrop

    Inventor： James M. Cook ,  Jeremy S. Waldrop

    IPC: B60T13/66 ,  B60T17/22 ,  B60T13/68

    CPC classification number: B60T13/665 ,  B60T17/228

    Abstract: An electronic pneumatic brake system for trains which significantly improves brake cylinder pressure build-up time and facilitates essentially instantaneous and simultaneous braking on all cars of the train. The electronic pneumatic brake system includes electronic pneumatic control valves on the cars which individually control the braking on each car or a pack of cars and which are regulated by an electronic pneumatic controller on each car that receives electronic braking and release signals by way of wireless communication from an electronic head end unit on the lead locomotive, or where no head end unit is provided in the locomotive, receives pneumatic braking signals through the brake pipe.

    Abstract translation: 一种用于火车的电子气动制动系统，其显着地提高制动缸压力建立时间，并且有助于在列车的所有车辆上基本上瞬时和同时的制动。 电子气动制动系统包括轿厢上的电子气动控制阀，其分别控制每辆汽车或一包汽车上的制动，并且由每个汽车上的电子气动控制器调节，所述电动气动控制器通过无线通信接收电子制动和释放信号 从机车上的电子头端单元或机车内没有设置头端单元，通过制动管接收气动制动信号。

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