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

IPC分类号： F41G7/00 ,  F41G7/22 ,  F41G7/26 ,  F41G7/28

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。

公开(公告)号：US4383661A

公开(公告)日：1983-05-17

申请号：US162303

申请日：1980-06-23

申请人： Philippe Ottenheimer ,  Pierre Haon

发明人： Philippe Ottenheimer ,  Pierre Haon

IPC分类号： F41G7/30 ,  F41G7/28

CPC分类号： F41G7/30

摘要： A ground station forming part of a system for controlling the flight of a missile comprises two cascaded computers, the first of these computers generating guidance instructions on the basis of initially available data while the second computer converts these instructions into control signals transmitted to the missile. A receiver aboard the missile translates these control signals into operating commands for missile-borne actuators affecting its course, e.g. motors controlling yaw and pitch through the positioning of aerodynamic surfaces; the responses of the actuators to the operating commands are monitored by negative-feedback loops including error-correcting networks.

摘要翻译： 形成用于控制导弹飞行的系统的一部分的地面站包括两个级联的计算机，这些计算机中的第一台计算机基于初始可用数据产生指导指令，而第二计算机将这些指令转换成传输到导弹的控制信号。 导弹上的接收器将这些控制信号转换成影响其航向的导弹执行器的操作命令，例如。 通过定位空气动力学表面控制偏航和俯仰的电机; 致动器对操作命令的响应由包括纠错网络的负反馈回路监控。

公开(公告)号：US10072908B2

公开(公告)日：2018-09-11

申请号：US14760546

申请日：2014-01-10

申请人： MBDA UK LIMITED

发明人： Nigel Stansfield

IPC分类号： F41G7/28 ,  F41G7/22 ,  G01S7/40 ,  G01S13/87 ,  G01S13/88 ,  G01S13/90 ,  G01S13/06 ,  G01S13/00

CPC分类号： F41G7/28 ,  F41G7/2246 ,  F41G7/2293 ,  G01S7/4004 ,  G01S13/06 ,  G01S13/878 ,  G01S13/883 ,  G01S13/904

摘要： In a method of guiding a missile in flight to a target (FIG. 1), the location of the missile and the range to the target are measured at a plurality of moments during the flight of the missile (step 10). The location of the target is calculated from the measured ranges and the measured missile locations (step 20). A required velocity vector angle is calculated from the calculated location of the target and a guidance law (step 30). A lateral acceleration required to provide the missile with a velocity oriented to the target at the required velocity vector angle is calculated for the missile (step 40). The missile is caused to accelerate with the calculated lateral acceleration, so that the missile to follows a trajectory according to the guidance law (step 50).

公开(公告)号：US20120268309A1

公开(公告)日：2012-10-25

申请号：US13024957

申请日：2011-02-10

申请人： Alphonso A. Samuel ,  Robert M. Pawloski ,  Nathan A. Goodman

发明人： Alphonso A. Samuel ,  Robert M. Pawloski ,  Nathan A. Goodman

IPC分类号： F41G7/28 ,  G01S13/00

CPC分类号： G01S13/90 ,  F41G7/2246 ,  F41G7/2286 ,  G01S13/726

摘要： Virtual Aperture Radar (VAR) imaging provides terminal phase radar imaging for an airborne weapon that can resolve multiple closely-spaced or highly correlated scatterers on a given target with a single pulse to provide an aimpoint update at a useful range to target without training data and without requiring a large aperture antenna. VAR imaging exploits the sparse, dominant-scatterer nature of man-made targets. The array manifold is constructed with a large number of basis functions that are parameterized by range or angle (or both) to target. The number of basis functions extends the capability to resolve scatterers beyond the Rayleigh resolution. However, this also makes the manifold underdetermined. A sparse reconstruction technique that places a sparsity constraint on the number of scatterers is used to solve the manifold to uniquely identify the ranges or angles to the scatterers on the target. These updates are passed to the weapon's guidance system, which in turn generates command signals to actuate aerodynamic surfaces such as fins or canards to steer the weapon to the target.

摘要翻译： 虚拟孔径雷达（VAR）成像为机载武器提供终端相位雷达成像，可以使用单个脉冲来解决给定目标上的多个紧密间隔或高度相关的散射体，以在无需训练数据的目标位置提供目标点更新， 而不需要大孔径天线。 VAR成像利用人为目标的稀疏，主要的散射体性质。 阵列歧管由大量基准函数构成，由基准函数的范围或角度（或两者）参数化为目标。 基础功能的数量扩展了解析散射体超出瑞利分辨率的能力。 然而，这也使得歧管未确定。 使用稀疏重建技术将稀疏约束放置在散射体数量上，以解决歧管，以唯一地识别目标上散射体的范围或角度。 这些更新被传递到武器的引导系统，该系统又产生命令信号来致动空气动力学表面，例如翅片或者胡子，以将武器转向目标。

公开(公告)号：US20100032514A1

公开(公告)日：2010-02-11

申请号：US12281047

申请日：2007-03-01

申请人： Henk Mentink

发明人： Henk Mentink

IPC分类号： F41G7/24 ,  F41G7/28

CPC分类号： G01S1/10 ,  F41G7/28

摘要： There is disclosed an apparatus and a method for guidance of a projectile. The method for guidance of a projectile, includes emission from the launching position of the projectile of beams pointing to the vertexes of a regular polygon, emission from the launching position of a beam encompassing the preceding beams, determination of position of the projectile relative to the beams, the determined position enabling to correct the projectile trajectory to maintain the projectile the closer to the center of the polygon formed by the beams.

摘要翻译： 公开了一种用于引导射弹的装置和方法。 用于引导射弹的方法包括从指向正多边形的顶点的射弹的发射位置的发射，包括前述射束的射束的发射位置的发射，射弹相对于射弹的位置的确定 光束，所确定的位置能够校正射弹轨迹，以使射弹更靠近由梁形成的多边形的中心。

公开(公告)号：US07498969B1

公开(公告)日：2009-03-03

申请号：US11701696

申请日：2007-02-02

申请人： Lee M. Paulsen ,  James B. West

发明人： Lee M. Paulsen ,  James B. West

IPC分类号： F41G7/28 ,  F42B15/01 ,  F42C13/04 ,  H01Q1/28 ,  G01S13/88 ,  H04B7/185

CPC分类号： F42C19/00 ,  F41G7/346 ,  G01S19/36 ,  H01Q1/281 ,  H01Q1/288 ,  H01Q9/0492 ,  H01Q9/30 ,  H01Q21/24

摘要： The present invention is directed to a fuze application capable of GPS (Global Positioning System) and proximity radar functionality by co-locating a proximity radar antenna with a GPS DRA (Dielectric Resonator Antenna) fuze. The GPS DRA fuze has a HE11δ mode structure resulting in an E-field null at the center. The monopole proximity radar antenna is mounted in the E-field null center and is thus electrically isolated from the GPS DRA fuze. The high dielectric constant permits the GPS DRA fuze to operate in the L1 frequency and the electrically shortened proximity radar antenna to resonate in the C-Band within a small form factor. The GPS DRA fuze maintains a forward-looking CP (circular polarization) pattern while proximity antenna maintains a desirable monopole pattern. Nesting allows mounting of both GPS and proximity radar antennas on the fuze nose while reducing the total space occupied.

摘要翻译： 本发明涉及一种通过使用GPS DRA（介电谐振器天线）引信来共同定位接近雷达天线的能够实现GPS（全球定位系统）和接近雷达功能的引信应用。 GPS DRA引信具有HE11delta模式结构，导致中心处的电场为零。 单极邻近雷达天线安装在电场无效中心，因此与GPS DRA引信电隔离。 高介电常数允许GPS DRA引信以L1频率工作，并且电气缩短的接近雷达天线在小波形内在C波段中谐振。 GPS DRA引信保持前瞻性CP（圆极化）图案，而接近天线保持期望的单极模式。 嵌套允许将GPS和接近雷达天线安装在引信鼻子上，同时减少占用的总空间。

公开(公告)号：US5366179A

公开(公告)日：1994-11-22

申请号：US94976

申请日：1993-07-22

申请人： Anton Manhalter

发明人： Anton Manhalter

IPC分类号： F42C13/04 ,  F41G7/28

CPC分类号： F42C13/045 ,  F42C13/042

摘要： A method of initiating the detonation of a warhead of a friendly guided missile and an arrangement for implementing the method. If a friendly guided missile or flying body, during its target approach phase, approaches an enemy missile or flying body, the active radar target seeker of the friendly guided missile is switched to perform a fine range discrimination, and an additional modulated signal is transmitted by the transmit/receive antenna of the active radar target seeker of the friendly guided missile, with this additional signal being received again after reflection at the enemy missile. With the aid of the received signal, the evaluation and control unit of the active radar target seeker generates an image of the enemy missile and determines the position of the warhead within the enemy missile. The warhead of the friendly guided missile is then guided into the vicinity of the warhead of the enemy missile and caused to explode. The friendly guided missile includes an active radar target seeker provided with a transmit/receive antenna, a high frequency component, an oscillator, a range gate filter bank and an evaluation and control unit.

摘要翻译： 启动引导友好导弹弹头的方法和实施该方法的安排。 如果友好的导弹或飞行器在目标进近阶段接近敌方导弹或飞行体，则转换友好导弹的主动雷达目标探测器进行精细范围鉴别，并且附加的调制信号通过 发射/接收天线的主动雷达目标探测器的友好导弹，这个附加信号在敌方导弹反射后再次被接收。 借助于接收到的信号，主动雷达目标探测器的评估和控制单元产生敌方导弹的图像，并确定弹头在敌方导弹内的位置。 友好导弹弹头被引导到敌方导弹附近，造成爆炸。 友好的导弹包括一个主动的雷达目标探测器，它配备有一个发射/接收天线，一个高频分量，一个振荡器，一个量程栅极滤波器组和一个评估和控制单元。

公开(公告)号：US5344099A

公开(公告)日：1994-09-06

申请号：US45144

申请日：1993-04-12

申请人： William C. Pittman ,  Susan D. Terrill

发明人： William C. Pittman ,  Susan D. Terrill

IPC分类号： F41G7/28 ,  F41G7/26

CPC分类号： F41G7/28

摘要： This invention is a beam rider system and method that utilizes polarization-agile millimeter beams. Information is spatially encoded in the beams by varying the rate of rotation of the linearly polarized vector of the beams. In one embodiment, information is encoded on a beam that is nutated around a centerline flight path of a missile. In another embodiment, information is encoded on four parallel beams that form a centerline which is the intended flight path of the missile. Receiver means in the flying missile receive and decode information from the beams and use this decoded information to guide the missile to a target.

摘要翻译： 本发明是利用偏振敏捷毫米波束的波束车载系统和方法。 信息通过改变光束的线性偏振矢量的旋转速率在光束中进行空间编码。 在一个实施例中，信息被编码在围绕导弹的中心线飞行路径章动的波束上。 在另一个实施例中，信息被编码在形成作为导弹的预定飞行路径的中心线的四条平行波束上。 飞行导弹中的接收机装置接收和解码来自波束的信息，并使用该解码的信息来将导弹引导到目标。

公开(公告)号：US09316463B2

公开(公告)日：2016-04-19

申请号：US14274427

申请日：2014-05-09

申请人： Rosemount Aerospace Inc.

发明人： William Durand

IPC分类号： F41G7/22 ,  F41G7/26 ,  F41G7/28 ,  F41G7/00 ,  G01S13/86 ,  H01Q1/38 ,  H01Q21/06 ,  H01Q5/22

CPC分类号： F41G7/26 ,  F41G7/008 ,  F41G7/2246 ,  F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  F41G7/28 ,  G01S13/867 ,  H01Q1/38 ,  H01Q5/22 ,  H01Q21/065

摘要： A multimode seeker includes a radio-frequency antenna and a controller. The radio-frequency antenna comprises a substrate and an electrically conductive film deposited on the substrate. The substrate is transparent to short wavelength infrared radiation. The electrically conductive film is configured to transmit and receive radio-frequency radiation and is transparent to the short wavelength infrared radiation. The controller is configured to receive and interpret data from the radio-frequency antenna.

摘要翻译： 多模探头包括射频天线和控制器。 射频天线包括基板和沉积在基板上的导电膜。 衬底对短波长红外辐射是透明的。 导电膜被配置为发射和接收射频辐射，并且对于短波长红外辐射是透明的。 控制器被配置为接收和解释来自射频天线的数据。

公开(公告)号：US20160003579A1

公开(公告)日：2016-01-07

申请号：US14760546

申请日：2014-01-10

申请人： MBDA UK LIMITED

发明人： Nigel STANSFIELD

IPC分类号： F41G7/28

CPC分类号： F41G7/28 ,  F41G7/2246 ,  F41G7/2293 ,  G01S7/4004 ,  G01S13/06 ,  G01S13/878 ,  G01S13/883 ,  G01S13/9035

摘要： In a method of guiding a missile in flight to a target (FIG. 1), the location of the missile and the range to the target are measured at a plurality of moments during the flight of the missile (step 10). The location of the target is calculated from the measured ranges and the measured missile locations (step 20). A required velocity vector angle is calculated from the calculated location of the target and a guidance law (step 30). A lateral acceleration required to provide the missile with a velocity oriented to the target at the required velocity vector angle is calculated for the missile (step 40). The missile is caused to accelerate with the calculated lateral acceleration, so that the missile to follows a trajectory according to the guidance law (step 50).

摘要翻译： 在将飞行中的导弹引导到目标（图1）的方法中，在导弹飞行期间的多个时刻测量导弹的位置和对目标的范围（步骤10）。 目标的位置由测量的距离和测得的导弹位置计算（步骤20）。 从目标的计算位置和引导律计算所需的速度矢量角（步骤30）。 计算导弹所需的横向加速度，用于以导弹将所需的速度向量角度定向到目标的速度提供给导弹（步骤40）。 引导导弹与计算出的横向加速度加速，使导弹按照指导原则遵循轨迹（步骤50）。