公开(公告)号：US20200057456A1

公开(公告)日：2020-02-20

申请号：US16369097

申请日：2019-03-29

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Shunsuke ARAKI

IPC: G05D1/12 ,  G05D1/00 ,  G05D1/10 ,  F41G7/34

Abstract: In a guiding device, a communication device receives a signal containing detection data of a target, and a processing unit. In the processing unit, a course setting section sets a flight course for a lofted flight based on the detection data, and a guiding section determines a progressing direction based on the flight course and outputs a guidance signal containing the progressing direction. The course setting section sets a first flight course when the flying object is launched. Also, the course setting section changes the first flight course to a second flight course based on the detection data after launching of the flying object.

公开(公告)号：US20190249957A1

公开(公告)日：2019-08-15

申请号：US16258777

申请日：2019-01-28

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Keisuke ANDO

IPC: F41G7/34 ,  F42B15/01 ,  G01S13/88 ,  G01S3/782 ,  G05D1/12

CPC classification number: F41G7/34 ,  F42B15/01 ,  G01S3/782 ,  G01S13/88 ,  G05D1/12

Abstract: A command control system includes an interception predicting section and an assigning section. The interception predicting section calculates a predicted intercept point of a target to be shot down and a guided missile to shoot down the target. The assigning section acquires first weather data of the predicted intercept point, and generates a launching instruction based on the first weather data so as to launch one of a first guided missile and a second guided missile as the guided missile. A method by which the first guided missile detects the target and a method by which the second guided missile detects the target are different.

公开(公告)号：US10323906B2

公开(公告)日：2019-06-18

申请号：US15281608

申请日：2016-09-30

Applicant: The Boeing Company

Inventor： Michelle V. DeJong

IPC: F41G7/34 ,  F42B15/01 ,  F42B33/06 ,  B64D1/04

Abstract: An autonomous flight termination system for terminating vehicle flight after the vehicle is launched from an aircraft includes a global positioning system (GPS) receiver; a termination unit selected from a cut-off switch connected to terminate vehicle flight when actuated, and a switch connected to detonate an explosive on the vehicle; a system controller for receiving a first signal indicating separation of the vehicle from the aircraft and a second signal from the GPS receiver to calculate an actual vehicle trajectory, and for sending a third signal to actuate the termination unit to terminate the flight of the vehicle when the actual vehicle trajectory is determined to be outside the safety bounds of a mission-planned flight trajectory; and a failsafe controller connected to receive operational data of the system controller, and to actuate the termination unit when the operational data indicates that the system is in an error state.

公开(公告)号：US10222178B1

公开(公告)日：2019-03-05

申请号：US14791054

申请日：2015-07-02

Applicant: Litel Instruments

Inventor： Robert O. Hunter, Jr. ,  Adlai H. Smith

IPC: F41G7/34 ,  G06T7/11 ,  G06T7/00 ,  G01S13/90 ,  G01S19/48 ,  G06G7/80

Abstract: A method of mapping a target region image to a referenced image includes steps of acquiring the target region image. The method also includes acquiring the referenced image overlapping the target region image. The method further includes determining a number of common subregions in an intersection of the referenced image and the target region image, determining offsets between the common subregions, computing a distortion map of the target region image over the intersection, and remapping the target region image to match the reference image. The method can be utilized in a Unmanned Aerial Vehicle (UAV) and the target image can be a SAR image.

公开(公告)号：US09852645B2

公开(公告)日：2017-12-26

申请号：US14828052

申请日：2015-08-17

Applicant: THE BOEING COMPANY

Inventor： Steven A. Wright

IPC: G08G5/00 ,  H04N5/247 ,  H04N5/33 ,  H04N7/18 ,  G01S19/39 ,  B64D47/08 ,  F41G7/20 ,  F41G7/34 ,  G01S5/16 ,  G05D1/00 ,  G06T7/73 ,  G01S19/15 ,  G01S19/18 ,  G01S19/48 ,  G06T7/70 ,  F41G7/36

CPC classification number: G08G5/0047 ,  B64D47/08 ,  F41G7/20 ,  F41G7/343 ,  F41G7/346 ,  F41G7/36 ,  G01S5/16 ,  G01S19/15 ,  G01S19/18 ,  G01S19/39 ,  G01S19/48 ,  G05D1/00 ,  G05D1/107 ,  G06T7/70 ,  G06T7/74 ,  G06T2207/10032 ,  G06T2207/30184 ,  G06T2207/30244 ,  H04N5/247 ,  H04N5/33 ,  H04N7/183

Abstract: Disclosed is a Global Positioning System (“GPS”) independent navigation system (“GINS”) for a self-guided aerial vehicle (“SAV”). The SAV has a housing, where the housing has an outer surface, a length, a front-end, and a longitudinal axis along the length of the housing. The GINS includes a first optical sensor, a second optical sensor, a storage unit, and a comparator.

公开(公告)号：US09423250B1

公开(公告)日：2016-08-23

申请号：US13593216

申请日：2012-08-23

Applicant: James J. Troy

Inventor： James J. Troy

IPC: G01C17/38 ,  G01C1/10 ,  G01C21/16 ,  F41G7/34 ,  G01C25/00 ,  B64F5/00 ,  G01S5/16

CPC classification number: G01C1/10 ,  B64F5/00 ,  F41G7/34 ,  F41G7/343 ,  G01C21/16 ,  G01C25/005 ,  G01S5/16

Abstract: A method includes initializing an inertial measurement unit (IMU) at a starting location and gathering acceleration and rotational data as the IMU is moved to an intermediate location. An indication that the IMU is at the intermediate location is received. The method includes gathering acceleration and rotational data as the IMU is moved to an ending location and calculating a position of the ending location based on a known position of the starting location and the acceleration data. The method includes calculating corrected acceleration data based on a difference between the calculated position of the ending location and a known position of the ending location, and calculating a position of the intermediate location based on the corrected acceleration data are provided.

Abstract translation: 一种方法包括在起始位置初始化惯性测量单元（IMU），并且当IMU移动到中间位置时收集加速度和旋转数据。 接收到IMU位于中间位置的指示。 该方法包括当IMU移动到结束位置时收集加速度和旋转数据，并且基于起始位置和加速度数据的已知位置来计算结束位置的位置。 该方法包括基于所计算的结束位置的位置与终止位置的已知位置之间的差异来计算校正的加速度数据，以及基于校正的加速度数据计算中间位置的位置。

公开(公告)号：US20160195878A1

公开(公告)日：2016-07-07

申请号：US14911469

申请日：2014-06-15

Applicant: RAFAEL ADVANCED DEFENSE SYSTEMS LTD

Inventor： Omri PELEG ,  Eran SHIMONOVITZ ,  Avfram LEVY

IPC: G05D1/10 ,  F41G7/34 ,  G05D1/00 ,  F42B15/01 ,  F41G7/22

CPC classification number: G05D1/107 ,  F41G7/007 ,  F41G7/008 ,  F41G7/2206 ,  F41G7/2213 ,  F41G7/2253 ,  F41G7/2293 ,  F41G7/30 ,  F41G7/343 ,  F42B15/01 ,  G01C21/12 ,  G01S5/16 ,  G05D1/0038

Abstract: The present invention relates to electro-optic guided missile systems and, in particular, it concerns systems and methods providing enhanced navigation capabilities based on ego-motion processing of seeker images. The missile system comprising: a missile; a seeker located at a nose portion of said missile, said seeker comprising an electro-optic imaging sensor; and a control arrangement for steering the missile along a flight path to a target, characterized in that the missile system further comprises: a navigation subsystem receiving images from said imaging sensor, said navigation subsystem being configured to: co-process a plurality of said images from said imaging sensor to derive ego-motion of said missile relative to a region viewed by said imaging sensor; derive from said ego-motion a calculated target direction from said missile to a target.

Abstract translation: 本发明涉及电光导弹系统，特别涉及提供基于探测器图像的自动运动处理的增强导航能力的系统和方法。 导弹系统包括：导弹; 位于所述导弹的鼻部的探测器，所述探测器包括电光成像传感器; 以及用于将导弹沿着飞行路径转向目标的控制装置，其特征在于，所述导弹系统还包括：导航子系统，从所述成像传感器接收图像，所述导航子系统被配置为：协同处理多个所述图像 从所述成像传感器导出所述导弹相对于由所述成像传感器观看的区域的自身运动; 从所述自我运动导出从所述导弹到目标的计算目标方向。

公开(公告)号：US09127913B2

公开(公告)日：2015-09-08

申请号：US12834867

申请日：2010-07-12

Applicant: Michael G. Neff ,  Shirley N. Cheng ,  Ted L. Johnson ,  Chang-Shaung R. Lee

Inventor： Michael G. Neff ,  Shirley N. Cheng ,  Ted L. Johnson ,  Chang-Shaung R. Lee

IPC: G01C21/00 ,  F41G7/34

CPC classification number: F41G7/343 ,  G01C21/00

Abstract: Route search planner methods and systems are described. In an embodiment, a probability map can be generated from previous sensor scans combined with a projected target location of relocatable targets in a target area. A route can be generated by a route generator, based at least in part on the probability map, and based on optimal system performance capabilities utilized to search for at least one of the relocatable targets. A search manager can then assign an evaluation criteria value to the route based on route evaluation criteria, and compare the evaluation criteria value to other evaluation criteria values corresponding to respective previously generated routes to determine an optimal route. The search manager can then determine whether to generate one or more additional routes and assign additional evaluation criteria values for comparison to determine the optimal route.

Abstract translation: 描述路线搜索计划方法和系统。 在一个实施例中，可以从与目标区域中的可重定位目标的投影目标位置组合的先前传感器扫描生成概率图。 可以至少部分地基于概率图，并且基于用于搜索可重定位目标中的至少一个的最佳系统性能能力，由路由生成器生成路由。 然后，搜索管理器可以基于路线评估标准向路线分配评估标准值，并将评估标准值与对应于先前生成的各路由的其他评估标准值进行比较，以确定最佳路由。 然后，搜索管理器可以确定是否生成一个或多个附加路线并分配附加的评估标准值以进行比较以确定最佳路线。

公开(公告)号：US08525088B1

公开(公告)日：2013-09-03

申请号：US13426114

申请日：2012-03-21

Applicant: Todd A. Ell ,  Robert D. Rutkiewicz

Inventor： Todd A. Ell ,  Robert D. Rutkiewicz

IPC: F41G7/34 ,  F41G7/00

CPC classification number: F41G7/007 ,  F41G3/145 ,  F41G7/2226 ,  F41G7/2253 ,  F41G7/2293

Abstract: A passive guidance system including a viewpoint capture system (VCS) including a first processor in communication with first memory and a first SWIR imager for creating a viewpoint image database having a plurality of images, at least one of the images having a target point. A weapon guidance module is in communication with the VCS and coupled to a weapon. The weapon guidance module includes a second processor in communication with second memory and a second SWIR imager for storing the viewpoint image database and correlating in-flight images from the second SWIR imager to provide guidance commands directing the weapon to the target point.

Abstract translation: 一种被动引导系统，包括包括与第一存储器通信的第一处理器的视点捕获系统（VCS）和用于创建具有多个图像的视点图像数据库的第一SWIR成像器，所述图像中的至少一个具有目标点。 武器指导模块与VCS通信并与武器相连。 武器引导模块包括与第二存储器通信的第二处理器和第二SWIR成像器，用于存储视点图像数据库，并将来自第二SWIR成像器的飞行中图像相关联，以提供将武器引导到目标点的指导命令。

公开(公告)号：US6135387A

公开(公告)日：2000-10-24

申请号：US156042

申请日：1998-09-07

Applicant: Wolfgang Seidel ,  Frank Guischard

Inventor： Wolfgang Seidel ,  Frank Guischard

IPC: F41G7/34 ,  F42B10/02 ,  F42B10/16 ,  F42B10/26

CPC classification number: F41G7/346 ,  F42B10/02 ,  F42B10/16 ,  F42B10/26

Abstract: A method for the autonomous guidance of a spin-stabilized artillery projectile (2; 25) toward a target (12). To ensure that an autonomously guided, spin-stabilized artillery projectile (2; 25) hits a target (12) with high precision, even at distances of .gtoreq.35 km, previously determined target data are transmitted to the projectile (2; 25) and stored therein before it is fired, and, following the firing of the projectile (2; 25), these stored data are compared with projectile position data, detected with the aid of a satellite navigational receiving station (23). The correction data resulting from this comparison are then used for the projectile (2; 25) guidance. Shortly before reaching the guidance phase, the velocity of the projectile is reduced by the use of spin-stabilized brakes and the projectile flight is changed for purposes of guidance from a spin-stabilized to a fin-stabilized flight state, wherein the projectile (2; 25) is then guided aerodynamically by means of rotating fins (9), arranged on the nose side, which can swing out, and wherein the spin-stabilized brakes function as lift surfaces once they are locked in place.

Abstract translation: 一种自动引导自转稳定炮弹（2; 25）朝向目标（12）的方法。 为了确保自主引导的自旋稳定的炮弹（2; 25）以高精度击中目标（12），即使在> / = 35公里的距离处，先前确定的目标数据被传输到射弹（2; 25 ）并在其被发射之前存储，并且在射弹（2; 25）射击之后，将这些存储的数据与在卫星导航接收站（23）的辅助下检测到的射弹位置数据进行比较。 然后将该比较产生的校正数据用于射弹（2; 25）指导。 在达到指导阶段之前不久，通过使用自旋稳定的制动器来减少弹丸的速度，并且为了从自旋稳定飞行状态到飞边稳定飞行状态的目的而改变射弹飞行，其中射弹（2 ; 25）然后通过设置在鼻侧的旋转翅片（9）被空气动力地引导，其可以摆出，并且其中旋转稳定的制动器一旦被锁定就位就起着提升面的作用。