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公开(公告)号：US10677565B2
公开(公告)日：2020-06-09
申请号：US15536619
申请日：2015-12-13
发明人： Tsafrir Avni
摘要： A guidance system for remote guidance of a remote platform(s) towards a target destination is disclosed. The guidance system includes a light module including a light source operable for beam to illuminating the remote platform, and a spatial light modulator (SLM) placed in the optical path of the light beam emitted from the light source. The guidance system includes a controller operable for obtaining data indicative of guidance information for navigating the remote platform towards the target destination. The controller operates the SLM to encode the guidance information in the light beam. The guidance information may be encoded in light pattern including at least one of the following: a spatial light pattern formed in a cross-section of the light beam, a temporal light pattern in the light beam, and a spatiotemporal light pattern. The guidance information is encoded in the light beam such that the remote platform can navigate towards the target by detecting at least a cross-sectional region of the light beam, decoding a portion of the guidance information encoded in the detected cross-sectional region and thereby determining guidance instructions for navigating the remote platform(s) towards the target destination.
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公开(公告)号：US20180245882A1
公开(公告)日：2018-08-30
申请号：US15536619
申请日：2015-12-13
发明人： Tsafrir Avni
摘要： A guidance system for remote guidance of a remote platform(s) towards a target destination is disclosed. The guidance system includes a light module including a light source operable for beam to illuminating the remote platform, and a spatial light modulator (SLM) placed in the optical path of the light beam emitted from the light source. The guidance system includes a controller operable for obtaining data indicative of guidance information for navigating the remote platform towards the target destination. The controller operates the SLM to encode the guidance information in the light beam. The guidance information may be encoded in light pattern including at least one of the following: a spatial light pattern formed in a cross-section of the light beam, a temporal light pattern in the light beam, and a spatiotemporal light pattern. The guidance information is encoded in the light beam such that the remote platform can navigate towards the target by detecting at least a cross-sectional region of the light beam, decoding a portion of the guidance information encoded in the detected cross-sectional region and thereby determining guidance instructions for navigating the remote platform(s) towards the target destination.
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3.发明授权Offset aperture gimbaled optical system with optically corrected conformal dome 有权带光学校正的保形圆顶的偏移孔径万向光学系统公开(公告)号：US09335126B2
公开(公告)日：2016-05-10
申请号：US13944267
申请日：2013-07-17
申请人： Raytheon Company
CPC分类号： F41G7/2213 , F41G7/2293 , F41G7/26 , G02B26/101 , G02B27/0037
摘要： An offset aperture gimbaled optical system comprises a gimbal and an optics assembly that is mounted on an inner gimbal and offset radially from an axis of symmetry (and rotation axis) of a conformal dome. An optical corrector adjacent the inner surface of the conformal dome encompasses the field-of-view of the optics assembly as the inner gimbal rotates about its rotation axis. The corrector is fixed with respect to the inner gimbal's rotation axis while it rotates about the axis of symmetry. The optical corrector comprises an aspheric transparent arch having an optical corrector shape and position responsive to a shape of the conformal dome at the offset position of the optics assembly. In different applications, the offset aperture provides for reduced optical aberrations and improved utilization of the available packaging volume to accommodate multiple offset aperture optics assemblies.
摘要翻译： 偏移光圈万向光学系统包括万向节和光学组件，该组件安装在内万向架上并且从保形圆顶的对称轴线（和旋转轴线）径向偏移。 当内部万向节绕其旋转轴线旋转时，邻近共形圆顶的内表面的光学校正器包围光学组件的视场。 校正器相对于内万向节的旋转轴线固定，同时围绕对称轴线旋转。 光学校正器包括非球面透明拱，其具有光学校正器形状和位置，其响应于光学组件的偏移位置处的共形圆顶的形状。 在不同的应用中，偏移孔径提供减小的光学像差和改善可用包装体积的利用以适应多个偏移光圈光学组件。
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公开(公告)号：US20120061508A1
公开(公告)日：2012-03-15
申请号：US12639735
申请日：2009-12-16
申请人： Gregoire de Viry , Guillaume Dupont
发明人： Gregoire de Viry , Guillaume Dupont
CPC分类号： B64C39/024 , B64C2201/121 , B64D1/04 , B64D7/08 , F41G3/145 , F41G3/22 , F41G7/226 , F41G7/2293
摘要： The present invention relates to the field of unmanned air vehicles, more commonly designated drone. More specifically, the invention applies to an armed drone system (10), notably equipped with a firing device and a steerable optronics ball (B) comprising means of illuminating targets (C).The invention proposes that the firing device be oriented towards the rear, so as to reduce the problems of masking of the optronics ball (B) by elements located in its line of sight, such as a front wheel (FW) for example. Moreover, because of operational use involving a phase (10S) for firing weapons and illuminating the target (C) from the back, the armed drone (10) moving away from the target, the vulnerability of the drone (10) is lessened.
摘要翻译： 本发明涉及无人驾驶飞行器领域，更常见的是无人驾驶飞机。 更具体地，本发明适用于特别装备有点火装置和可转向光电子球（B）的武装无人机系统（10），其包括照明目标（C）的装置。 本发明提出了射击装置朝向后方，从而通过例如前轮（FW）等位于其视线内的元件来减少光电球（B）的掩蔽问题。 此外，由于涉及使用武器的阶段（10S）和从后面照射目标（C）的操作使用，武装无人机（10）远离目标，所以无人机（10）的脆弱性被减轻了。
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公开(公告)号：US20090314878A1
公开(公告)日：2009-12-24
申请号：US12438826
申请日：2007-09-03
申请人： Dov Raviv
发明人： Dov Raviv
CPC分类号： F41F3/04 , F41G7/008 , F41G7/2246 , F41G7/2286 , F41G7/308 , F41H11/02 , F42B15/01 , F42B15/10
摘要： An interception system for intercepting incoming missiles and/or rockets including a launch facility, a missile configured to be launched by the launch facility, the missile having a fragmentation warhead, a ground-based missile guidance system for guiding the missile during at least one early stage of missile flight and a missile-based guidance system for guiding the missile during at least one later stage of missile flight, the missile-based guidance system being operative to direct the missile in a last stage of missile flight in a head-on direction vis-a-vis an incoming missile or rocket.
摘要翻译： 拦截进入的导弹和/或火箭的拦截系统，包括发射设施，配置为由发射设施发射的导弹，具有分裂弹头的导弹，在至少一个早期引导导弹的地面导弹导弹系统 导弹飞行阶段和在导弹飞行至少一个后期指导导弹的导弹导向系统，基于导弹的导弹系统可以在导弹飞行的最后阶段直接引导导弹 相对于进来的导弹或火箭。
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6.发明授权
公开(公告)号：US6138944A
公开(公告)日：2000-10-31
申请号：US310675
申请日：1999-04-16
IPC分类号： F41G7/26
CPC分类号： F41G7/26
摘要： The scatterider guidance system is mounted on the flying object that is toe guided toward a more direct impact on the selected target. The system utilizes a designating beam of laser pulses that is emitted from the launch pad toward the target and atmospheric particles that scatter the laser pulses to calculate the guidance commands that lead the flying object to follow the laser beam closely. Upon detection by the scatterider sensors of the laser light that is scattered by the atmospheric particles, the perpendicular radial distance between the laser beam and the longitudinal axis of the object in flight is calculated by the onboard guidance electronics and subsequently used to generate the deflection commands. The deflection commands, in turn, are used to deflect aerodynamic control surfaces of the object such that the object approaches and stays close to the laser beam. This guidance system is activated as soon after launch as possible and continues until the object impacts on the target.
摘要翻译： 散射器引导系统安装在要被引导以对所选择的目标更直接影响的飞行物体上。 该系统使用从发射台朝向目标射出的激光脉冲的指定光束和散射激光脉冲的大气颗粒，以计算引导飞行物体紧密跟随激光束的引导命令。 在由散射体传感器检测到由大气颗粒散射的激光的情况下，激光束与飞行中的物体的纵向轴线之间的垂直径向距离由机载引导电子计算，随后用于产生偏转命令 。 偏转指令又用于偏转物体的空气动力学控制表面，使得物体靠近并保持靠近激光束。 该指导系统在启动后尽快启动，并持续到对象对目标的影响。
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公开(公告)号：US6076765A
公开(公告)日：2000-06-20
申请号：US2370
申请日：1998-01-02
申请人： Tibor G. Horwath
发明人： Tibor G. Horwath
CPC分类号： G01S3/788 , F41G7/222 , F41G7/2253 , F41G7/2293
摘要： A reticle for a guidance seeker for spinning projectiles comprises a substrate; a pattern of a plurality of alternating light modulating structures, such as opaque and light transmitting, or light absorbing and light reflecting areas on the substrate such that an image of a target moving on the substrate will generate a plurality of pulses corresponding to the number of lines crossed by the image, the number of pulses increasing as the image moves outwardly from the center of the reticle; and a distinguishable, unambiguous, and singly periodic feature of the pattern, which is readily detectable every time the target image moves circumferentially, completing a full circle around the center of the reticle.
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公开(公告)号：US6060703A
公开(公告)日：2000-05-09
申请号：US107009
申请日：1998-06-29
CPC分类号： F41G7/226 , F41G7/008 , F41G7/2246 , F41G7/2293 , G01S13/86
摘要： The present invention is directed to an unfocused optical sensor including a dual mode optical and radio frequency (RF) sensor system for use with a guidance system of a munition. The inventive system comprises an optical sensor comprising a plurality of optical detector units. The optical detector units each produce an optical detector output signal upon illumination with optical energy. In a dual mode embodiment, the sensor may further comprise an optional rf sensor which produces an rf sensor output signal. In the case of the dual mode sensor, the optical detector units are arranged in an annulus mounted coaxially with the transreflector and twist reflector about the longitudinal axis of the munition. The sensor system further comprises a signal processor operably associated with the optional rf sensor and the optical sensor to receive the rf sensor and optical detector output signals and provide a guidance signal to the guidance system.
摘要翻译： 本发明涉及一种未聚焦的光学传感器，其包括用于与弹药的引导系统一起使用的双模光和射频（RF）传感器系统。 本发明的系统包括包括多个光学检测器单元的光学传感器。 光学检测器单元在用光能照射时各自产生光学检测器输出信号。 在双重模式实施例中，传感器还可以包括可选的rf传感器，其产生rf传感器输出信号。 在双模式传感器的情况下，光学检测器单元布置在与反射器和扭转反射器围绕弹药的纵向轴线同轴安装的环形空间中。 传感器系统还包括与可选的rf传感器和光学传感器可操作地相关联的信号处理器，以接收rf传感器和光学检测器输出信号并向引导系统提供引导信号。
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公开(公告)号：US5702068A
公开(公告)日：1997-12-30
申请号：US79479
申请日：1979-09-25
申请人： Alfred Stoll , Wolfgang Gulitz , Hans Tessari , Reiner Eckhardt
发明人： Alfred Stoll , Wolfgang Gulitz , Hans Tessari , Reiner Eckhardt
CPC分类号： F41G7/2253 , F41G7/2213 , F41G7/2293
摘要： In a seeker head a field of view is scanned cyclically for providing picture informations referenced to a seeker-fixed coordinate system. The seeker carries a gyro assembly, which provides attitude variation signals as a function of attitude variations of the seeker relative to inertial space. The attitude variation signals are applied to a coordinate transformer which transforms all picture informations with their addresses into an inertial coordinate system which coincided with the seeker-fixed coordinate system after the completion of the preceding scan. Thereby during each scan all picture informations are transformed into one single inertial coordinate system. After the completion of the scan, the picture informations are again transformed into an inertial coordinate system, which coincided with the seeker-fixed coordinate system at the end of said scan, and are stored in a memory. This is the same coordinate system into which the picture informations will be transformed during the next-following scan. Thus at the end of this next-following scan the picture informations from two consecutive scans are available, which are referenced to one single, common coordinate system and are therefore comparable in spite of attitude variations of the seeker. These picture informations are applied to signal processing means, such as a target selection logic.
摘要翻译： 在寻求者头部，周期地扫描视野，以提供参考寻找者固定坐标系的图像信息。 探测器携带一个陀螺仪组件，该陀螺仪组件提供作为探测器相对于惯性空间的姿态变化的函数的姿态变化信号。 姿态变化信号被施加到坐标变换器，该坐标变换器将其地址的所有图像信息变换成在完成前一次扫描之后与寻轨器固定坐标系一致的惯性坐标系。 因此，在每次扫描期间，所有图像信息都被转换为单个惯性坐标系。 扫描完成后，图像信息再次变换为惯性坐标系，该坐标系与扫描结束时的寻轨器固定坐标系一致，并存储在存储器中。 这是在下一次扫描期间图像信息将被转换的相同坐标系。 因此，在接下来的下一次扫描结束时，来自两个连续扫描的图像信息是可用的，其参考一个单一的公共坐标系，因此尽管寻求者的姿态变化是可比的。 这些图像信息被应用于诸如目标选择逻辑的信号处理装置。
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公开(公告)号：US5647559A
公开(公告)日：1997-07-15
申请号：US498651
申请日：1995-07-06
申请人： Rudolf Romer , Gerd Wollmann , Helmut Misoph
发明人： Rudolf Romer , Gerd Wollmann , Helmut Misoph
摘要： An apparatus for flight path correction of flying bodies, such as projectiles, rockets and the like, with the aid of a laser guide beam, wherein the course of the respective flying body is determined and processed in a measuring apparatus associated with the firing apparatus and containing an optical receiving detector in order to obtain an appropriate correction signal, and wherein the correction signal is then transmitted, through encoding of the laser guide beam, to a receiving apparatus disposed in the tail portion of the flying body. To determine the course of the flying body in a simple manner, both an optical light source for producing a light beam and an optical receiving detector are disposed on the measuring apparatus, and triple reflector or mirror elements, that reflect the incident light beam back in its initial direction independently of the respective angle of incidence, are disposed on the bottom of the flying body or at the ends of the guiding mechanism of the flying body. In rotating flying bodies, the triple mirror elements are preferably distributed at irregular intervals in a circle, perpendicular to the longitudinal axis of the flying body. This arrangement makes it possible to use the signals reflected by the triple mirror elements to determine the roll position of the respective flying body.
摘要翻译： 借助于激光引导梁，用于飞行物体如射弹，火箭等的飞行路径校正的装置，其中相应飞行体的过程在与射击装置相关联的测量装置中被确定和处理， 包含光接收检测器以获得适当的校正信号，并且其中通过激光引导光束的编码将修正信号传输到设置在飞行体的尾部的接收装置。 为了以简单的方式确定飞行体的路线，在测量装置上设置用于产生光束的光学光源和光学接收检测器，并且将入射光束反射回来的三重反射镜或反射镜元件 其独立于相应入射角的初始方向设置在飞行体的底部或飞行体的引导机构的端部。 在旋转的飞行体中，三重镜元件优选地以垂直于飞行体的纵向轴线的圆圈以不规则的间隔分布。 这种布置使得可以使用由三重镜元件反射的信号来确定相应飞行体的滚动位置。
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