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。

公开(公告)号：US20100214154A1

公开(公告)日：2010-08-26

申请号：US12390331

申请日：2009-02-20

Applicant: Frank A. Birdsong, JR. ,  Lloyd E. Kinsey, JR.

Inventor： Frank A. Birdsong, JR. ,  Lloyd E. Kinsey, JR.

IPC: G01S13/00

CPC classification number: G01S7/412 ,  G01S7/024 ,  G01S7/282 ,  G01S13/887

Abstract: There is disclosed a system and method for detecting targets. A transmitter may transmit a first inverse transform signal, the first inverse transform signal derived from a reference image of a first reference target at a first aspect angle. A receiver may receive a return signal reflected from a scene. A detector may determine, based on the return signal, if an object similar to the first target at the first aspect angle is detected within the scene.

Abstract translation: 公开了用于检测目标的系统和方法。 发射机可以以第一方位角度发送第一逆变换信号，该第一反变换信号是从第一参考目标的参考图像导出的第一逆变换信号。 接收机可以接收从场景反射的返回信号。 检测器可以基于返回信号确定在场景内是否检测到与第一方位角相似的第一目标物体。

公开(公告)号：US20100032516A1

公开(公告)日：2010-02-11

申请号：US12203302

申请日：2008-09-03

Applicant: THOMAS A. OLDEN ,  Robert Cavalleri ,  Lloyd E. Kinsey, JR.

Inventor： THOMAS A. OLDEN ,  Robert Cavalleri ,  Lloyd E. Kinsey, JR.

IPC: F42B10/62 ,  F42B15/01 ,  B64C30/00

CPC classification number: F42B10/64 ,  F42B10/668

Abstract: A solid-fuel pellet thrust and control actuation system (PT-CAS) provides command authority for maneuvering flight vehicles over subsonic and supersonic speeds and within the atmosphere and exo-atmosphere. The PT-CAS includes a chamber or solid-fuel pellets that are ignited to expel gas through a throat. The expelled gas is directed at supersonic vehicle speeds in atmosphere to a cavity between an aero control surface and the airframe to pressurize the cavity and deploy the surface or at subsonic speeds in atmosphere or any speed in exo-atmosphere allowed to flow out a through-hole in the surface where the throat and through-hole provide a virtual converging/diverging nozzle to produce a supersonic divert thrust. A pellet and control actuation system (P-CAS) Without the through-hole provides command authority at supersonic speeds in atmosphere. A restrictor mechanism controls the bleed of pressurized gas from the cavity to the external environment to achieve a deployment time objective for either the PT-CAS or P-CAS.

Abstract translation: 固体燃料颗粒推力和控制致动系统（PT-CAS）为在亚音速和超音速下以及大气和大气中的机动飞行器提供了指挥权力。 PT-CAS包括被点燃以通过喉部排出气体的室或固体燃料颗粒。 排出的气体以大气中的超音速车辆速度被引导到航空控制表面和机身之间的空腔，以对空腔加压并且在大气中以亚音速的速度或在外部空气中的任何速度下展开通孔， 喉部和通孔的表面中的孔提供虚拟的会聚/发散喷嘴以产生超音速转向推力。 没有通孔的颗粒和控制致动系统（P-CAS）在大气中的超音速速度下提供命令权限。 限流器机构控制加压气体从空腔排放到外部环境，以实现PT-CAS或P-CAS的部署时间目标。