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。

公开(公告)号：US07990308B2

公开(公告)日：2011-08-02

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: G01S7/41

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：US08193476B2

公开(公告)日：2012-06-05

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: F42B15/01

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空气控制表面和机身之间的空腔，以对空腔加压并且将其表面或亚音速的速度在大气中或任何外部气氛的速度流出， 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）在大气中以超音速速度提供命令权限。 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。

公开(公告)号：US07093788B2

公开(公告)日：2006-08-22

申请号：US10891588

申请日：2004-07-15

Applicant: James G. Small ,  Donald J. Lacey ,  Lloyd E. Kinsey, Jr. ,  Mark V. Zepeda

Inventor： James G. Small ,  Donald J. Lacey ,  Lloyd E. Kinsey, Jr. ,  Mark V. Zepeda

IPC: B64C27/16

CPC classification number: B64C39/00

Abstract: A rotating wing aircraft has a rotating fuselage and wings. The aircraft is configured to rotate with the air passing over the wings because of the rotation providing the lift needed to keep the aircraft aloft. The wings have rudders coupled to them, such as at the tips of the wings, to provide force for laterally moving the aircraft. The aircraft may be able to remain airborne by hovering for a long period of time, on the order of days. Power for the aircraft may be provided by a central diesel electric generator, which provides power for electric motors that turn propellers that are on the wings. The aircraft may be used for any of a variety of applications, such as for surveillance, communications, or as a radar platform.

Abstract translation: 旋翼机具有旋转的机身和机翼。 飞机被配置为随着空气通过机翼而旋转，因为旋转提供了使飞机保持高空所需的升力。 机翼具有与它们相连的方向舵，例如在翼的顶端，以提供用于横向移动飞行器的力。 飞机可以通过在几天的时间内长时间徘徊而保持机载。 飞机的动力可以由中央柴油发电机提供，该发电机为转动在机翼上的螺旋桨的电动机提供动力。 该飞机可用于任何各种应用，例如用于监视，通信或作为雷达平台。