公开(公告)号：US07111619B2

公开(公告)日：2006-09-26

申请号：US10758437

申请日：2004-01-15

Applicant: Arthur J. Schneider

Inventor： Arthur J. Schneider

IPC: F41B6/00

CPC classification number: F41B6/003

Abstract: An electromagnetic coil gun system includes a launcher having a barrel with a longitudinal bore therethrough, and a plurality of longitudinally extending electrical excitation coils arranged circumferentially around the bore of the barrel so that a magnetic field produced by an electrical current in each electrical excitation coil penetrates into the bore. Each electrical excitation coil is independently activated by the electrical current passed therethrough. There is a projectile sized to be received within the bore of the barrel and having a circumferential armature at a tail end thereof, and a nose end. The projectile placed into the bore is fired by producing a traveling sequence of propulsive currents in the electrical excitation coils moving in a direction from the breech end toward the muzzle end of the barrel, so that a traveling propulsive magnetic field produced by the electrical excitation coils interacts with the armature of the projectile to propel the projectile in the direction from the breech end toward the muzzle end of the barrel. Simultaneously, a traveling sequence of field-nulling currents in the electrical excitation coils moves in the direction from the breech end toward the muzzle end of the barrel but closer to the muzzle end of the barrel than the traveling sequence of propulsive currents and spatially leading the traveling sequence of propulsive currents. The field-nulling currents are in a circumferential direction opposite to the propulsive currents, thereby at least partially nulling the traveling propulsive magnetic field at the nose end of the projectile.

Abstract translation: 电磁线圈枪系统包括具有穿过其中的纵向孔的筒的发射器，以及围绕筒的孔周向布置的多个纵向延伸的电激励线圈，使得由每个电激励线圈中的电流产生的磁场穿透 进入孔。 每个电激励线圈由通过的电流独立地激活。 存在尺寸被设置成容纳在筒的孔内并且在其尾端具有圆周衔铁并且具有鼻端的射弹。 放置在孔中的弹丸通过在电激励线圈中沿着从后枪端朝向枪管的枪口端移动的方向产生一个推进电流的行进序列来发射，使得由电激励线圈产生的行进推进磁场 与弹丸的电枢相互作用，以便将射弹从枪支末端向枪口的枪口端推进。 同时，电激励线圈中的场归零电流的行进序列沿着枪管的后膛端朝向枪口端部的方向移动，但是比推进电流的行进顺序更靠近枪管端部，并且在空间上引导 推进电流行驶顺序。 场归零电流在与推进电流相反的圆周方向上，从而至少部分使在抛射体的鼻端处的行进推进磁场为零。

公开(公告)号：US5455587A

公开(公告)日：1995-10-03

申请号：US97298

申请日：1993-07-26

Applicant: Arthur J. Schneider

Inventor： Arthur J. Schneider

IPC: F41G7/22 ,  G01S7/20 ,  G01S7/41 ,  G01S13/88 ,  G01S13/89 ,  G01S13/00

CPC classification number: F41G7/2246 ,  F41G7/2286 ,  G01S7/414

Abstract: An improved imaging system. The inventive imaging system (10) is adapted to transmit a plurality of first radar signals at millimeter wave frequencies at an area including an object along with background clutter. The return signals are processed to provide a three dimensional image for applications demanding visibility through fog, haze, smoke and other obscurants. Such applications include enhanced vision for helicopters, ships, buses, trucks, traffic observation stations for an intelligent highway or security cameras for plants and military installations. In a guidance system application, for example, the inventive system would include an electronically scanning antenna (12) to provide range and amplitude signals representative of a target area. The range and amplitude signals (18, 20) are compared to stored signals (26, 30) to create the three dimensional image. The stored signals are selected for comparison based on the dive angle of the missile (28, 32). The three dimensional image is then processed (22, 24, 34, 36, 38, 40) to derive guidance commands for the missile.

Abstract translation: 改进的成像系统。 本发明的成像系统（10）适于在包括物体的区域和背景杂波的毫米波频率处发射多个第一雷达信号。 处理返回信号以提供三维图像，用于要求通过雾，雾，烟雾和其它遮瑕物的可见性的应用。 这种应用包括对直升机，船舶，公共汽车，卡车，智能公路交通观测站或植物和军事设施的安全摄像机的增强视力。 在引导系统应用中，例如，本发明的系统将包括电子扫描天线（12），以提供表示目标区域的范围和幅度信号。 将范围和幅度信号（18,20）与存储的信号（26,30）进行比较以产生三维图像。 根据导弹的潜水角度（28,32）选择存储的信号进行比较。 然后处理三维图像（22,24,34,36,38,40），以导出导弹的指导命令。

公开(公告)号：US06910657B2

公开(公告)日：2005-06-28

申请号：US10448869

申请日：2003-05-30

Applicant: Arthur J. Schneider

Inventor： Arthur J. Schneider

IPC: F41G7/30 ,  G01S11/08 ,  G01S13/87 ,  F41G7/00 ,  F41G7/20

CPC classification number: G01S11/08 ,  F41G7/303 ,  G01S13/46 ,  G01S13/878 ,  G01S2013/466

Abstract: A vehicle guidance system. The system includes a first mechanism for tracking a vehicle based on time-of-arrival information associated with energy emanating from the vehicle and providing vehicle position information in response thereto. A second mechanism steers the vehicle based on the vehicle position information. In a specific embodiment, the system of further includes a third mechanism for locating the target based on time-of-arrival information associated with energy radiating from the target and providing target location information in response thereto. The second the second mechanism steers the vehicle based on the target location information and the vehicle position information.

Abstract translation: 车辆引导系统 该系统包括用于基于与从车辆发出的能量相关联的到达时间信息跟踪车辆的第一机构，并响应于此提供车辆位置信息。 第二机构基于车辆位置信息来引导车辆。 在具体实施例中，所述系统还包括用于基于从目标辐射的能量相关联的到达时间信息来定位目标的第三机制，并响应于此提供目标位置信息。 第二机构基于目标位置信息和车辆位置信息来引导车辆。

公开(公告)号：US06614012B2

公开(公告)日：2003-09-02

申请号：US09795577

申请日：2001-02-28

Applicant: Arthur J. Schneider ,  Ralph H. Klestadt ,  David A. Faulkner

Inventor： Arthur J. Schneider ,  Ralph H. Klestadt ,  David A. Faulkner

IPC: F42B1522

CPC classification number: F41G7/305

Abstract: A precision-guided hypersonic projectile weapon system. The inventive system includes a first subsystem for determining a target location and providing data with respect thereto. A second subsystem calculates trajectory to the target based on the data. The projectile is then launched and guided in flight along the trajectory to the target. In the illustrative application, the projectile is a tungsten rod and the first subsystem includes a forward-looking infrared imaging system and a laser range finder. The second subsystem includes a fire control system. The fire control system includes an optional inertial measurement unit and predicts target location. The projectile is mounted in a missile launched from a platform such as a vehicle. After an initial burn, the missile launches the projectile while in flight to the target. The missile is implemented with a rocket with a guidance system and a propulsion system. In accordance with the present teachings, the guidance system includes a transceiver system mounted on the projectile. The transceiver system includes a low-power continuous wave, millimeter wavelength wave emitter. A system is included at the launch platform for communicating with the projectile. The platform system sends a blinking command to the projectile and measures the round trip delay thereof to ascertain the range of the projectile. Velocity is determined by conventional Doppler techniques or differentiation. Azimuth and elevation are then determined by a monopulse antenna on the launch platform. As a consequence, the platform ascertains the location of the projectile and the impact point thereof. The platform generates a command to the projectile which is received by the projectile and used to actuate control surfaces to adjust the trajectory and impact point thereof as necessary.

Abstract translation: 精准导弹超音速射弹武器系统。 本发明的系统包括用于确定目标位置并相对于其提供数据的第一子系统。 第二子系统基于数据计算目标的轨迹。 然后，弹道沿着轨迹向飞行中发射和引导到目标。 在说明性应用中，抛射体是钨棒，第一子系统包括前视红外成像系统和激光测距仪。 第二个子系统包括消防系统。 消防控制系统包括可选的惯性测量单元，并预测目标位置。 射弹安装在从诸如车辆的平台发射的导弹中。 在最初的燃烧之后，导弹在飞行到达目标时发射弹体。 导弹采用带导向系统和推进系统的火箭实施。 根据本教导，引导系统包括安装在射弹上的收发器系统。 收发器系统包括低功率连续波，毫米波长波发射器。 在发射平台上包括一个与射弹通信的系统。 平台系统向射弹发出闪烁命令，测量往返延迟，以确定射弹的射程。 速度由传统的多普勒技术或差异化决定。 然后通过发射平台上的单脉冲天线确定方位角和高程。 因此，平台确定了射弹的位置及其影响点。 该平台产生一个由弹丸接收的弹道的命令，用于激活控制面以根据需要调整其轨迹和撞击点。

公开(公告)号：US06300898B1

公开(公告)日：2001-10-09

申请号：US09480957

申请日：2000-01-10

Applicant: Arthur J. Schneider ,  James G. Small

Inventor： Arthur J. Schneider ,  James G. Small

IPC: H04B7185

CPC classification number: H04K3/92 ,  G01S19/015 ,  G01S19/09 ,  G01S19/11 ,  G01S19/18 ,  G01S19/21 ,  H04K3/255 ,  H04K3/28 ,  H04K3/90 ,  H04K2203/22 ,  H04K2203/24

Abstract: A missile guidance system designed to operate on GPS signals in an anti-jamming environment. The inventive system includes first, second and third airborne vehicles (20). A GPS receiver (24) is mounted on each of the three vehicles (20) to receive signals transmitted from spaceborne satellites (14). Each vehicle (20) acts as a pseudo-satellite or ‘pseudolite’. The received GPS signals are processed by a processor (26) to provide a first intermediate signal indicating the position of the vehicle (20). This signal is retransmitted from each vehicle and received by a GPS receiver mounted on a missile. The received intermediate signal is processed on the missile to provide an output signal indicating the position thereof. The pseudolites would be airborne in the vicinity of a target area. Because the pseudolites are relatively close to the targets compared to a satellite in high altitude orbit and because the pseudolites would be able to transmit a kilowatt or more power, the signal strength may be improved significantly. To succeed as a jammer, a jammer, successful against GPS satellites, would need considerably more power to succeed against aircraft carried pseudolites. The pseudolite system delivers GPS signals into the target area 40-70 dB stronger than signals coming directly from GPS satellites. By timing the signals for 100% time coverage, enemy C/A code receivers will be jammed because they are limited to a J/S capability of 30 dB.

Abstract translation: 导弹引导系统设计用于在抗干扰环境中对GPS信号进行操作。 本发明的系统包括第一，第二和第三机载车辆（20）。 GPS接收器（24）安装在三个车辆（20）中的每一个上，以接收从星载卫星（14）发射的信号。 每个车辆（20）用作伪卫星或“伪卫星”，所接收的GPS信号由处理器（26）处理以提供指示车辆（20）的位置的第一中间信号，该信号从每个 由导弹安装的GPS接收机接收，接收到的中间信号在导弹上进行处理，提供一个表示其位置的输出信号，伪卫星将在目标区域附近空中传播，因为伪卫星相对较近 与高空轨道的卫星相比，由于伪卫星能够传输千瓦或更大的功率，所以信号强度可能会大大提高。作为干扰器成功，干扰器将成功应对GPS卫星，将需要 相对于成功的飞机携带伪卫星的能力要大得多，伪卫星系统将GPS信号传输到目标区域，比直接来到的信号强40-70 dB m GPS卫星。 通过对100％时间覆盖的信号定时，敌方C / A码接收机将被卡住，因为它们被限制在30dB的J / S能力。

公开(公告)号：US5537909A

公开(公告)日：1996-07-23

申请号：US423391

申请日：1995-04-17

Applicant: Arthur J. Schneider ,  James G. Small ,  Donald E. French ,  Henry August

Inventor： Arthur J. Schneider ,  James G. Small ,  Donald E. French ,  Henry August

IPC: F42B10/56 ,  B64D1/04 ,  F42B12/36 ,  F42B15/00 ,  G01S3/782 ,  G01S13/89

CPC classification number: B64D1/04 ,  F42B12/365

Abstract: A bomb damage assessment system that is carried by a weapon and released to provide imagery of a bombed area before and after bomb delivery. The system comprises a glider that is releasably secured to the weapon that includes tracking and guidance electronics for programmably controlling the flight thereof. An imaging system is disposed in the front end of the glider and a deployable ballute is disposed at the rear end thereof. A data link is provided for transmitting images to a command center for review. The system provides imagery of a target area before, during and after weapon impact. Television or infrared cameras may be used for day or night missions. As a target area is approached, the glider is released, is decelerated by the ballute, wings are unfolded, and the ballute is released, resulting in an aerodynamic vehicle that flies much slower than the weapon. The imaging system tracks the weapon to impact. The explosion of the weapon produces a hot spot that is tracked by the imaging system. The hot spot is tracked until a preselected depression angle is reached. The glider banks until the hot spot is at a predetermined angle relative to the centerline thereof. This results in a spiral glide path around the hot spot so that the target area is viewed from all aspects. The spiral path also results in a monotonically decreasing range to the hot spot. The glider may employ a GPS receiver, and the target location in GPS coordinates may be entered into the guidance and control system. The glider may be programmed to fly along a specific path or geometric surface in GPS coordinates toward the target. Using a fixed field of view imaging system, a large amount of background is seen from long range and better linear resolution is obtained at short range until the glider descends to the ground. Bomb damage assessment may be performed at the command center within minutes of weapon impact.

Abstract translation: 炸弹损伤评估系统，由武器携带并被释放，以在炸弹传送前后提供轰炸区域的图像。 该系统包括可释放地固定到武器上的滑翔机，其包括用于可编程地控制其飞行的跟踪和引导电子装置。 成像系统设置在滑翔机的前端，并且可展开的小球在其后端设置。 提供数据链接用于将图像发送到指挥中心进行审查。 该系统在武器冲击之前，之中和之后提供目标区域的图像。 电视或红外摄像机可用于白天或夜间任务。 当接近目标区域时，滑翔机被释放，由球道减速，机翼展开，气球被释放，产生飞行比武器慢得多的空气动力学车辆。 成像系统跟踪武器的影响。 武器的爆炸产生了由成像系统跟踪的热点。 跟踪热点直到达到预选的俯角。 滑翔机直到热点相对于其中心线处于预定角度。 这导致围绕热点的螺旋滑动路径，使得从各个方面观察目标区域。 螺旋路径也导致热点单调减少的范围。 滑翔机可以使用GPS接收机，并且GPS坐标中的目标位置可以被输入到引导和控制系统中。 滑翔机可以被编程为沿GPS坐标向着目标的特定路径或几何表面飞行。 使用固定视野成像系统，从远距离看到大量的背景，并且在短距离内获得更好的线性分辨率，直到滑翔机下降到地面。 炸弹伤害评估可能在武器冲击的几分钟内在指挥中心进行。

公开(公告)号：US07913606B2

公开(公告)日：2011-03-29

申请号：US11867098

申请日：2007-10-04

Applicant: Arthur J. Schneider ,  Andrew J. Hinsdale

Inventor： Arthur J. Schneider ,  Andrew J. Hinsdale

IPC: F42C17/04

CPC classification number: F42C11/04 ,  F42C17/04

Abstract: The present invention generally concerns inductive power transfer systems and their components. More particularly, representative and exemplary embodiments of the present invention generally relate to systems, devices and methods for transferring modulated current between a launcher and at least one guided missile.

Abstract translation: 本发明一般涉及感应电力传输系统及其部件。 更具体地，本发明的代表性和示例性实施例通常涉及用于在发射器和至少一个导弹之间传递调制电流的系统，装置和方法。

公开(公告)号：US07795567B2

公开(公告)日：2010-09-14

申请号：US11100243

申请日：2005-04-05

Applicant: Arthur J. Schneider

Inventor： Arthur J. Schneider

IPC: F42B10/12

CPC classification number: F41G7/301 ,  F42B10/64 ,  F42B12/06 ,  F42B15/01

Abstract: The disclosed system, device and method for guiding a hypersonic kinetic penetrator projectile (300) generally includes a kinetic penetrator body (110, 230) and a slip-over electronic guidance unit (120, 220), where the kinetic penetrator body slidably mounts through the slip-over electronic guidance unit. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve accuracy and control of a hypersonic projectile. Exemplary embodiments of the present invention generally provide multi-use slip-over electronic guidance units for hypersonic kinetic penetrator projectiles in 105 mm and 120 mm munition rounds, surface-to-surface missiles, and air-to-surface missiles.

Abstract translation: 用于引导超音速动力穿透器射弹（300）的所公开的系统，装置和方法通常包括动力穿透体（110,230）和滑动式电子引导单元（120,220），其中动力穿透体可滑动地安装穿过 滑动电子引导单元。 公开的特征和规格可以被不同地控制，适应或以其他方式任意地修改以提高超音速射弹的精度和控制。 本发明的示例性实施例通常提供用于105mm和120mm弹药弹，地对地导弹和空对地导弹的超音速动力穿透器射弹的多用途滑移电子引导单元。

公开(公告)号：US5685504A

公开(公告)日：1997-11-11

申请号：US474862

申请日：1995-06-07

Applicant: Arthur J. Schneider ,  Kenneth R. Johnson ,  Henry August ,  Douglas E. Elerath ,  Paul D. Shubert

Inventor： Arthur J. Schneider ,  Kenneth R. Johnson ,  Henry August ,  Douglas E. Elerath ,  Paul D. Shubert

IPC: F41G7/30 ,  F41G7/20

CPC classification number: F41G7/305 ,  F41G7/303

Abstract: A system for guiding the flight of a projectile to a target. The system comprises a tracking and guidance system, the projectile, and a projectile reference and control system that is part of the projectile. The tracking and guidance system includes a target tracker, a projectile tracker for providing a projectile-tracking laser beam, and a target designator for designating the target using a target-tracking laser beam, and for providing range data indicative of the range to the target. A processor is coupled to the target designator, the target tracker, and the projectile tracker for processing target and projectile return signals and target range signals to generate an actuator command signal that is transmitted by the projectile tracker using the projectile-tracking laser beam and that is used to alter the flight of the projectile. The projectile reference and control system includes an optical reference including polarized and unpolarized retroflectors for reflecting the projectile-tracking laser beam back to the projectile tracker, and a detector that is responsive to the projectile-tracking laser beam provided by the projectile tracker, for detecting the actuator command signal transmitted by the projectile tracker. A command operated actuator is coupled to the detector for processing the actuator command signal and for generating a trajectory modification signal that is used to alter the flight of the projectile. A divert assembly coupled to the command operated actuator for generating thrust that diverts the trajectory of the projectile in response to the trajectory modification signal.

Abstract translation: 一种将射弹飞行到目标的系统。 该系统包括跟踪和引导系统，射弹和作为射弹一部分的射弹参考和控制系统。 跟踪和引导系统包括目标跟踪器，用于提供射弹跟踪激光束的射弹跟踪器，以及用于使用目标跟踪激光束指定目标的目标指示器，以及用于将指示范围的范围数据提供给目标 。 处理器耦合到目标指示符，目标跟踪器和射弹跟踪器，用于处理目标和射弹返回信号和目标范围信号，以产生由射弹跟踪器使用射弹跟踪激光束传输的致动器命令信号，并且 用于改变射弹的飞行。 射弹参考和控制系统包括一个光学参考，包括用于将射弹跟踪激光束反射回射弹跟踪器的偏振和非偏振反射器，以及响应于由射弹跟踪器提供的射弹跟踪激光束的检测器，用于检测 执行器命令信号由射弹跟踪器传输。 命令操作的致动器耦合到检测器，用于处理致动器命令信号并且用于产生用于改变射弹飞行的轨迹修改信号。 耦合到命令操作致动器的转向组件，用于产生响应于轨迹修改信号转移射弹轨迹的推力。

公开(公告)号：US20110083547A1

公开(公告)日：2011-04-14

申请号：US12972600

申请日：2010-12-20

Applicant: Arthur J. Schneider ,  Andrew J. Hinsdale

Inventor： Arthur J. Schneider ,  Andrew J. Hinsdale

IPC: F42C17/04

CPC classification number: F42C11/04 ,  F42C17/04

Abstract: Embodiments of an inductive power transfer method are generally described herein. In some embodiments, a method of transferring data and power to a plurality of guided projectiles located in launcher tubes on a helicopter is described herein. In some embodiments, power and data are inductively transferred across the launcher windings to the projectile windings to configure the control systems of the guided projectiles to provide a lock-on-before-launch capability.

Abstract translation: 感应功率传输方法的实施例在此通常被描述。 在一些实施例中，这里描述了将数据和功率传送到位于直升机上的发射管中的多个引导的射弹的方法。 在一些实施例中，功率和数据通过发射器绕组感应地传递到射弹绕组，以配置引导的射弹的控制系统以提供启动前锁定功能。