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    Trajectory shaping of anti-armor missiles via tri-mode guidance
    71.
    发明授权
    Trajectory shaping of anti-armor missiles via tri-mode guidance 失效
    通过三模式导弹进行防弹导弹的轨迹成形

    公开(公告)号：US4277038A

    公开(公告)日：1981-07-07

    申请号：US034088

    申请日：1979-04-27

    Applicant: Robert E. Yates ,  John P. Leonard ,  Robert E. Alongi ,  Wilfredo V. Albanes ,  Charles M. Bishop

    Inventor： Robert E. Yates ,  John P. Leonard ,  Robert E. Alongi ,  Wilfredo V. Albanes ,  Charles M. Bishop

    IPC: F41G7/00 ,  F41G7/22 ,  F41G7/34 ,  F42B15/02

    CPC classification number: F41G7/008 ,  F41G7/22 ,  F41G7/2253 ,  F41G7/226 ,  F41G7/2293 ,  F41G7/343

    Abstract: In a missile system, a simple way to guide a missile in a predetermined tectory from launch to the impacting with a target for optimum warhead penetration of armor by a guided missile. Initially, the missile is guided in yaw by proportional navigation. Subsequently it is guided in pitch first by a pitch programmer until the missile reaches a predetermined gimbal angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a pseudo-time-optimal closed loop controller to direct the missile pitch attitude at a predetermined rate toward a target until said missile reaches another predetermined gimbal angle, and finally by proportional navigation in pitch of the missile to the target.

    Abstract translation: 在导弹系统中，一种简单的方法来指导导弹在预定轨迹上从发射到受到导弹的最佳弹头穿透铠甲的目标。 最初，导弹通过比例导航在偏航中引导。 随后，它由音高编程员首先由音高引导，直到导弹达到导弹的探测器的视线与导弹的中心线之间的预定的万向角，然后通过伪时间最优的闭环控制器 以预定的速率朝向目标直接引导导弹俯仰姿态，直到所述导弹达到另一个预定的万向角，最后通过导弹到目标的俯仰比例导航。

    System for transmitting light signals between a missile and a missile control station
    72.
    发明授权
    System for transmitting light signals between a missile and a missile control station 失效
    用于在导弹和导弹控制站之间传输光信号的系统

    公开(公告)号：US4096380A

    公开(公告)日：1978-06-20

    申请号：US704029

    申请日：1976-07-09

    Applicant: Kurt Eichweber

    Inventor： Kurt Eichweber

    IPC: F41G7/22 ,  F41G7/30 ,  F42B12/38 ,  H04B9/00

    CPC classification number: F41G7/30 ,  F41G7/008 ,  F41G7/2206 ,  F41G7/2253 ,  F41G7/2293 ,  F42B12/387

    Abstract: A system for transmitting light signals between a missile and a missile control launching site is provided by utilizing a laser beam light signal transmission path. The system comprises a laser emitter having a relatively broad transmission beam for producing a transmission path for the modulated light signals during the flight of the missile. The system obviates the need for light transmission lines or other physical connection between the missile and the control station and provides for continuously aiming the laser beam on the missile by means of a follow-up device responsive to a portion of the beam reflected from the missile. At least one crown of triple mirror reflectors is distributed about the axis of the missile to enable the missile to reflect the laser beam impinging thereon independently of the flight position of the missile. The laser beam is modulated to transmit control light signals from the control station and information light signals from the missile.

    Abstract translation: 通过利用激光束光信号传输路径提供用于在导弹和导弹控制发射位置之间传输光信号的系统。 该系统包括具有相对宽的发射光束的激光发射器，用于在导弹飞行期间产生用于调制光信号的传输路径。 该系统避免了对导弹和控制站之间的光传输线路或其他物理连接的需要，并且通过响应于从导弹反射的一部分光束的后续装置连续地将激光瞄准在导弹上 。 三重反射镜的至少一个冠部围绕导弹的轴线分布，使得导弹能够反射其上独立于导弹的飞行位置而入射的激光束。 激光束被调制以从控制台传输控制光信号和来自导弹的信息光信号。

    Gun-launched glide vehicle with a mid-course and terminal guidance control system
    73.
    发明授权
    Gun-launched glide vehicle with a mid-course and terminal guidance control system 失效
    带有中程和终端指导控制系统的GUN-LAUNCHED GLIDE VEHICLE

    公开(公告)号：US3695555A

    公开(公告)日：1972-10-03

    申请号：US3695555D

    申请日：1970-06-12

    Applicant: US NAVY

    Inventor： CHADWICK WILLIAM R

    IPC: F41G7/22 ,  F41G7/14 ,  F41G7/06

    CPC classification number: F41G7/22 ,  F41G7/008 ,  F41G7/226 ,  F41G7/2293 ,  F41G7/30

    Abstract: The system comprises an eight-inch full-bore glide vehicle having retractable aerodynamic lifting surfaces which increase range performance and accuracy. The glide vehicle can be fired to a maximum range of 135 miles without guidance or to a range of 100 miles with accurate terminal guidance. An infrared horizon scanner provides feedback information to small bang-bang servooperated roll-tabs for vehicle despin and roll-attitude stabilization. Target acquisition occurs from the glide path with ship-based radar providing information for mid-course lateral guidance control. A forward observer illuminates the target with laser energy and the vehicle homes in on the target using bangbang monoplane control.

    Abstract translation: 该系统包括具有可伸缩空气动力提升表面的八英寸全孔滑行车辆，其提高了距离性能和精度。 滑翔车可以在135英里的最大范围内进行射击，无需指导，也可以通过准确的终端指导来射程达到100英里。 红外地平线扫描仪为小型爆炸式伺服操作滚动片提供反馈信息，用于车辆定位和侧倾姿势稳定。 目标获取发生在滑行路径上，船载雷达提供了中期横向引导控制的信息。 前方观察员用激光能量照射目标，并且使用轰炸单翼平面控制将车辆置于目标上。

    SEEKER/DESIGNATOR HANDOFF SYSTEM FOR USE IN DUAL-MODE GUIDED MISSILES
    78.
    发明申请
    SEEKER/DESIGNATOR HANDOFF SYSTEM FOR USE IN DUAL-MODE GUIDED MISSILES 审中-公开

    公开(公告)号：US20180080740A1

    公开(公告)日：2018-03-22

    申请号：US15269601

    申请日：2016-09-19

    Applicant: Rosemount Aerospace Inc.

    Inventor： Todd Ell

    IPC: F41G7/26 ,  F41G7/22

    CPC classification number: F41G7/26 ,  F41G3/145 ,  F41G7/008 ,  F41G7/2246 ,  F41G7/226 ,  F41G7/2293

    Abstract: Apparatus and associated methods relate to a dual-mode seeker for a guided missile equipped with seeker/designation handoff capabilities. The dual-mode seeker has Semi-Active Laser (SAL) and Image InfraRed (IIR) modes of operation. SAL-mode operation includes detecting laser pulses reflected by a target designated by a remote Laser Target Designator (LTD) and determining target direction using the detected laser pulses. SAL-mode operation also includes determining the Pulse Repetition Interval (PRI) of the detected laser pulses, and predicting timing of future pulses generated by the LTD. IIR-mode operation includes capturing Short-Wavelength InfraRed (SWIR) images of a scene containing the designated target and determining target location using one or more image features associated with the designated target. After the target direction can be determined using the IIR-mode of operation, an illuminator projects a signal onto the designated target so as to communicate to a remote operator that LTD target designation can be suspended.

    Target-designation detection used to shutter camera images for locating target
    79.
    发明授权
    Target-designation detection used to shutter camera images for locating target 有权

    公开(公告)号：US09857145B1

    公开(公告)日：2018-01-02

    申请号：US15195594

    申请日：2016-06-28

    Applicant: Rosemount Aerospace Inc.

    Inventor： Robert Rutkiewicz ,  Gary Halama

    IPC: F41G7/26 ,  H04N5/33 ,  H04N5/04 ,  F41G7/00

    CPC classification number: F41G7/26 ,  F41G7/008 ,  F41G7/2253 ,  F41G7/226 ,  F41G7/2293 ,  G01S3/784 ,  H04N5/04 ,  H04N5/30 ,  H04N5/33

    Abstract: Apparatus and associated methods relate to a seeker for a Semi-Active Laser (SAL) guided missile. The seeker has a Short-Wave InfraRed (SWIR) camera and a Pulse Timing Logic (PTL) detector. The PTL detector has a SWIR photo detector axially aligned with a lens stack of the SWIR camera. The SWIR photo detector is configured to detect a sequence of SWIR pulses generated by a SAL target designator and reflected by a designated target. The PTL detector has a pulse timer configured to identify a sequence pattern of the detected sequence of SWIR pulses, and to predict a timing of a next SWIR pulse in the identified sequence pattern so as to synchronize exposure of the SWIR camera to capture a next image of the designated target at the predicted timing of the next SWIR pulse. Such exposure timing can advantageously improve the signal to noise ratio of the next image.

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