公开(公告)号：US11971731B2

公开(公告)日：2024-04-30

申请号：US17577992

申请日：2022-01-18

Applicant: Rosemount Aerospace Inc.

Inventor： Guy Squillace ,  Gary Willenbring ,  Todd A. Ell

IPC: F41G7/22 ,  F41G7/34 ,  G05D1/00

CPC classification number: G05D1/107 ,  F41G7/2206 ,  F41G7/2233 ,  F41G7/2246 ,  F41G7/346

Abstract: A method and system for coordination of a plurality of munitions in a Global Positioning System (GPS) denied attack of a plurality of ground targets. A relative position of each munition is determined relative to the other munitions in the salvo and a distance range is determined of each munition relative to the other munitions in the salvo. A constellation formation is determined for the plurality of munitions in the salvo relative to a target seeker basket such that each munition in the constellation formation is navigated to its respective target seeker basket, whereby a change in navigation for each munition is caused when necessary such that each munition arrives at its determined seeker basket at an approximate same time.

公开(公告)号：US11774544B2

公开(公告)日：2023-10-03

申请号：US16469954

申请日：2017-11-29

Applicant: BAE SYSTEMS plc

Inventor： Andrew James Smith ,  Martin John White ,  Guiseppe Carlos Sarno

IPC: G01S5/02 ,  F42B15/01 ,  G01S1/08 ,  F41G7/34 ,  F42C13/04 ,  G01S1/02 ,  G01S5/00 ,  G01S5/14 ,  G01S11/10 ,  G01S19/18 ,  G05D1/10

CPC classification number: G01S5/0246 ,  F42B15/01 ,  G01S1/08 ,  G01S5/0242 ,  F41G7/34 ,  F42C13/04 ,  G01S1/028 ,  G01S5/0045 ,  G01S5/14 ,  G01S11/10 ,  G01S19/18 ,  G05D1/107

Abstract: According to an aspect of the invention, there is provided a control system for controlling a projectile, the control system comprising: a plurality of transmitters, wherein each transmitter of the plurality of transmitters is arranged to transmit an electromagnetic wave from a transmission position; a receiver associated with the projectile, the receiver being arranged to receive a plurality of electromagnetic waves transmitted from the plurality of transmitters; a controller associated with the projectile, the controller being arranged to: determine at least one of a position, a velocity or an acceleration of the projectile from transmission positions of the plurality of transmitters and Doppler measurements derived from the received plurality of electromagnetic waves; and generate a control signal for performing an action with the projectile depending on the determined at least one of position, velocity or acceleration of the projectile.

公开(公告)号：US20230056472A1

公开(公告)日：2023-02-23

申请号：US17406754

申请日：2021-08-19

Applicant: Raytheon Company

Inventor： Julie A. Graham ,  Brian A. Gin ,  Emile M. Szlemko

IPC: F41G7/00 ,  F41G7/34 ,  G06T7/70

Abstract: A system includes and maintains a machine learning algorithm. The machine learning algorithm is trained to identify non-targets in an environment. The system receives an image of the environment, and identifies the non-targets in the image using the trained machine learning algorithm. The system then generates a firing cut out map for overlaying on the image of the environment based on the identified non-targets in the image of the environment.

公开(公告)号：US20210262765A1

公开(公告)日：2021-08-26

申请号：US17183821

申请日：2021-02-24

Applicant: MBDA Deutschland GmbH

Inventor： Wolfgang SCHLOSSER

IPC: F41G7/22 ,  F41G7/34

Abstract: The present invention relates to a computer-implemented method for targeting missiles, to a corresponding computer program, to a corresponding computer-readable medium and to a corresponding data processing device, as well as to a missile.

公开(公告)号：US10436554B2

公开(公告)日：2019-10-08

申请号：US15411324

申请日：2017-01-20

Applicant: Northrop Grumman Innovation Systems, Inc.

Inventor： James Kolanek ,  Behshad Baseghi ,  David Sharpin ,  Anthony Visco ,  Falin Shieh

IPC: F41G7/34 ,  G05D1/08 ,  F42B15/10 ,  F42B15/01 ,  F41G7/30 ,  F41G7/00 ,  F42B10/66 ,  F41H11/02 ,  F42B10/00

Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

公开(公告)号：US20160047628A1

公开(公告)日：2016-02-18

申请号：US13839637

申请日：2013-03-15

Applicant: Orbital ATK, Inc.

Inventor： James Kolanek ,  Behshad Baseghi ,  David Sharpin ,  Anthony Visco ,  Falin Sheih

IPC: F41G7/34 ,  F42B15/10 ,  G05D1/08 ,  F42B15/01

CPC classification number: F41G7/34 ,  F41G7/007 ,  F41G7/303 ,  F41H11/02 ,  F42B10/66 ,  F42B15/01 ,  F42B15/105 ,  G05D1/0808

Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

Abstract translation: 实施例包括用于空中平台的主动保护系统和方法。 车载系统包括雷达模块，检测空中平台威胁范围内的飞行器，并确定是否有任何空中飞行器是空中威胁。 车载系统还确定到空中威胁的拦截矢量，将拦截矢量传达到弹出车辆，并使弹出车辆从空中平台弹出以拦截空中威胁。 弹出车辆包括对准推进器，以使喷射车辆的纵向轴线旋转以与拦截矢量基本对准，火箭发动机沿着拦截矢量加速喷射车辆，使推进器沿大致垂直于垂直方向的方向转向喷射车辆 拦截矢量和姿态控制推进器来调整喷射车的姿态。

公开(公告)号：US20150330744A1

公开(公告)日：2015-11-19

申请号：US14653100

申请日：2013-12-17

Applicant: NEXTER SYSTEMS

Inventor： Sylvain Muller

IPC: F41G7/00 ,  G01S17/89 ,  F41G7/34 ,  G01S17/10

CPC classification number: F41G7/007 ,  F41A19/00 ,  F41G1/473 ,  F41G3/06 ,  F41G3/14 ,  F41G7/346 ,  F42C17/04 ,  G01S17/10 ,  G01S17/102 ,  G01S17/89

Abstract: A method for acquiring the coordinates of a trigger point of a projectile above a field part on which a target is located, including: emission of at least one laser pulse having a pre-determined duration and directed towards the target; reception of the images reflected with a receiver equipped for the synchronous visualization of the laser pulses originating from a piece of observation of the field part; recovery of the coordinates of a desired trigger point when the operator has chosen a location after the piece of observation was moved. The invention also relates to a fire-control system using such a method.

Abstract translation: 一种用于获取在目标所位于的场部分之上的射弹的触发点的坐标的方法，包括：发射具有预定持续时间并指向目标的至少一个激光脉冲; 接收由接收器反射的图像，所述接收器被配备用于同步可视​​化源自场部分的观察的激光脉冲; 当操作者已经选择了观察条件之后的位置移动时，恢复所需触发点的坐标。 本发明还涉及使用这种方法的消防系统。

公开(公告)号：US6069584A

公开(公告)日：2000-05-30

申请号：US988307

申请日：1997-12-10

Applicant: Mark W. Johnson

Inventor： Mark W. Johnson

IPC: F41G7/34 ,  G01S5/14 ,  G01S19/09 ,  G01S19/39 ,  H04B7/185 ,  F42B15/01

CPC classification number: G01S19/11 ,  F41G7/346 ,  G01S19/18 ,  G01S19/41

Abstract: A system for monitoring guiding and controlling an unmanned, unteathered flight vehicle, generally assumed to be moving through the atmosphere of the earth at a high rate of speed. The system comprised an on-board positional receiver and processing means coupled to a transceiver capable of combining such positional information with additional data relative to the health and status of the flight vehicle and transmitting the same to a ground station of compatible and simplified design. A preferred positional determination means is to utilize a form for GPS signal thereby affording one the opportunity to include appropriate processing software or additional componentry if necessary for base station purposes and thereby provide a relatively inexpensive system having a low probability of detection for intercept that simultaneously yields vastly improved operating performance characteristics over the mere translation of received GPS signals to down-link or to remote stations as known in the prior art. The system of the present invention may be utilized to provide auto-registration correction, range-only correction, or a combination of auto-registration and range correction.

Abstract translation: 一种用于监控指导和控制无人驾驶飞机的系统，通常被认为是以高速率通过地球大气移动。 该系统包括车载位置接收器和耦合到收发器的处理装置，该收发机能够将这样的位置信息与相对于飞行器的健康状态和状态的附加数据相结合并将其发送到兼容和简化设计的地面站。 优选的位置确定装置是利用一种用于GPS信号的形式，从而提供一个机会，以便在基站目的需要时包括适当的处理软件或附加组件，从而提供一种相对便宜的系统，其具有低的拦截概率，同时产生 如现有技术中已知的，将接收到的GPS信号简单地转换为下行链路或远程站的操作性能特征大大改善。 本发明的系统可用于提供自动对位校正，仅范围校正，或自动对位和范围校正的组合。

公开(公告)号：US5857644A

公开(公告)日：1999-01-12

申请号：US199365

申请日：1988-05-13

Applicant: Manfred Kusters

Inventor： Manfred Kusters

IPC: F41G7/34 ,  F41G7/00

CPC classification number: F41G7/343

Abstract: The invention describes a target approach procedure for a guided, mobile missile for use against ground targets, particularly bridges, roads, rail junctions, hangars, shelters, command posts, harbor installations as well as ships, in which the missile is released at a great distance from the target and flies automatically to the target, with guidance by parallel lines that characterize ground structures, and hits it from the most favorable approach direction.

Abstract translation: 本发明描述了用于针对地面目标，特别是桥梁，道路，轨道交界处，机库，庇护所，指挥所，港口设施以及船舶的导弹，移动导弹的目标进近程序，其中导弹发射在一个伟大的 距离目标的距离，并自动飞行到目标，由平行线引导，表征地面结构，并从最有利的进近方向击中目标。

公开(公告)号：US5788179A

公开(公告)日：1998-08-04

申请号：US740414

申请日：1996-10-29

Applicant: Dallas C. Wicke

Inventor： Dallas C. Wicke

IPC: F41G7/30 ,  F41G7/34 ,  F41G7/36

CPC classification number: F41G7/306

Abstract: An ignition delay timing system, and corresponding method, for adjusting the position of an in-flight missile during its boost phase along its flight path according to a pre-launch flight path solution. The ignition delay system of the present invention is applied by navigating missile position between burnout of a given booster stage and ignition of a subsequent booster stage, and modifying ignition time of the subsequent boost stage so that the missile position along its flight path follows a pre-launch solution after all booster stages are burned. Nominal missile coast phases, which occur between burnout of one booster stage and ignition of subsequent booster stage are either increased or decreased for earlier or later booster stage ignitions to maintain the missile position along its flight path in accordance with the pre-launch solution.

Abstract translation: 一种点火延迟定时系统及相应的方法，用于根据预先启动的飞行路线解决方案，在其升降阶段沿其飞行路径调整飞行中导弹的位置。 本发明的点火延迟系统通过导航导弹位置在给定的增压级的燃尽和后续增压级的点火之间进行导航，并修改随后增压级的点火时间，使得沿其飞行路径的导弹位置遵循预先 所有增压阶段燃烧后的初始解决方案。 根据预发射解决方案，在一个升压级的怠速和后续增压级的点火之间发生的额定导弹海岸阶段，对于早期或后期的增压级点火进行增加或减少，以保持沿其飞行路径的导弹位置。