专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US10077971B1 Risley prism line-of-sight control for strapdown missile 有权
公开(公告)号：US10077971B1
公开(公告)日：2018-09-18
申请号：US12168664
申请日：2008-07-07
申请人： Gene D. Tener , Andrew H. Hawkins
发明人： Gene D. Tener , Andrew H. Hawkins
IPC分类号： F41G7/22 , F41G7/00
CPC分类号： F41G7/22 , F41G7/2226 , F41G7/2253 , F41G7/2293 , G01S3/785 , G01S3/786
摘要： An optical system and method comprising refracting light with a pair of Risley prisms and employing a line-of-sight control unit to adjust the pair.

2. 发明授权

US09347743B2 Offset aperture dual-gimbaled optical system 有权
标题翻译：偏移光圈双平衡光学系统
公开(公告)号：US09347743B2
公开(公告)日：2016-05-24
申请号：US13944378
申请日：2013-07-17
申请人： Raytheon Company
发明人： Chadwick B. Martin , David J. Knapp , Gregory P. Hanauska
IPC分类号： G02B27/00 , F41G7/22 , F41G7/26 , F41G7/20 , G02B26/10
CPC分类号： F41G7/2213 , F41G7/20 , F41G7/22 , F41G7/2293 , F41G7/26 , G02B26/101 , G02B27/0025
摘要： An offset aperture two-axis gimbaled optical system comprises a two-axis gimbal and an optics assembly that is mounted on the inner gimbal and offset radially from the rotation axis of the outer gimbal. The optics assembly is suitably offset so that its optical aperture does not overlap the rotation axis of the outer gimbal and its optical aperture is symmetric about the rotation axis of the inner gimbal. 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：偏移孔径双轴平衡光学系统包括两轴万向架和光学组件，其安装在内万向架上并且从外万向节的旋转轴线径向偏移。光学组件适当地偏移，使得其光学孔不与外部万向架的旋转轴线重叠，并且其光学孔径关于内部万向架的旋转轴线对称。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。

3. 发明授权

US09285190B1 Correlation/estimation reporting engagement system and method 有权
标题翻译：相关/估计报告制度和方法
公开(公告)号：US09285190B1
公开(公告)日：2016-03-15
申请号：US14026661
申请日：2013-09-13
申请人： Lockheed Martin Corporation
发明人： Jonathan A. Boardman , Jeffrey B. Boka , Naresh R. Patel
IPC分类号： F41G7/22 , F41G7/00
CPC分类号： F41G7/008 , F41G7/22 , F41G7/2206 , F41G7/2246 , F41G7/2253 , F41G7/2286 , F41G7/2293 , F41G7/301 , G01S13/726 , G01S13/867
摘要： A system and method for performing correlation processing for identifying an object of interest in a cloud of remote objects of different types comprises receiving RF and IR measurement data including rotational, translational bias and noise errors and determining and removing biases by minimizing a weighted distance metric. Correlation pairing metrics are then determined according to a maximum likelihood criteria. This method produces a correlation solution that minimizes the effects of biases and random noise while accounting for the statistical properties of the parameters being estimated.
摘要翻译：用于执行用于识别不同类型的远程对象的云中的感兴趣对象的相关处理的系统和方法包括：接收包括旋转，平移偏差和噪声误差的RF和IR测量数据，并且通过最小化加权距离度量来确定和消除偏差。然后根据最大似然准则确定相关配对度量。该方法产生一个相关解决方案，最大限度地减少偏差和随机噪声的影响，同时考虑所估计参数的统计特性。

4. 发明申请

US20150253111A1 SEMI-ACTIVE LASER SEEKER SYNCHRONIZATION 审中-公开
标题翻译：半主动激光锯片同步
公开(公告)号：US20150253111A1
公开(公告)日：2015-09-10
申请号：US14170773
申请日：2014-02-03
申请人： Rosemount Aerospace Inc.
发明人： William Caplan
IPC分类号： F41G7/22
CPC分类号： F41G7/22 , F41G3/145 , F41G7/007 , F41G7/226 , F41G7/2293
摘要： A system for semi-active laser seeker synchronization includes a laser target designator configured to emit a laser pulse signal and a seeker configured to detect the emitted signal from the laser target designator. The laser target designator and the seeker are operatively connected to synchronize the emission of the laser pulse signal and the detection of the seeker.
摘要翻译：用于半主动激光探测器同步的系统包括被配置为发射激光脉冲信号的激光目标指示符和被配置为检测来自激光目标指示符的发射信号的探测器。激光瞄准器和探测器可操作地连接以使激光脉冲信号的发射和探测器的检测同步。

5. 发明授权

US08519312B1 Missile with shroud that separates in flight 有权
标题翻译：导弹与护罩在飞行中分离
公开(公告)号：US08519312B1
公开(公告)日：2013-08-27
申请号：US12696123
申请日：2010-01-29
申请人： Paul A. Merems
发明人： Paul A. Merems
IPC分类号： B64G1/52 , H01Q1/42 , B64G1/00 , F41G7/22 , H01Q1/00
CPC分类号： F42B10/46 , F41G7/22 , F42B15/34 , F42B15/36
摘要： A missile includes a separable shroud that covers a nose portion of the fuselage of the missile. The shroud covers and protects a seeker window and a seeker at the nose of the missile. The shroud is configured to remain coupled to the missile during and immediately after launch of the missile, and to separate during flight under the action of aerodynamic forces. Toward that end parts of the shroud are initially coupled together by a retainer, which allows the parts to separate during flight. The retainer may include one or more tension bands that break at a certain tension, and/or one or more weakened parts of the shroud, which break during flight. Parts of the shroud may include inward protrusions that make contact with an ogive portion of the nose of the fuselage.
摘要翻译：导弹包括覆盖导弹机身的鼻部的可分离的护罩。护罩覆盖并保护导弹窗口和导弹鼻子上的寻求者。导弹被配置为在导弹发射期间和发射后立即与导弹保持耦合，并在空气动力作用下飞行期间分离。通过保持器将护罩的最后部分最初连接在一起，这使得部件在飞行过程中分离。保持器可以包括在一定张力下断裂的一个或多个张力带，和/或护罩的一个或多个弱化部分，其在飞行期间断裂。护罩的一部分可以包括与机身的鼻部的有效部分接触的向内突起。

6. 发明授权

US07795565B2 Guidance system with varying error correction gain 有权
标题翻译：引导系统具有不同的纠错增益
公开(公告)号：US07795565B2
公开(公告)日：2010-09-14
申请号：US11968705
申请日：2008-01-03
申请人： Gregory F. Bock
发明人： Gregory F. Bock
IPC分类号： F41G7/22 , F42B15/01 , F41G7/00 , F42B15/00
CPC分类号： F42B15/01 , F41G7/22 , G05D1/12
摘要： A guided missile or projectile and associated guidance control are provided to control a path to a point of intersection with a potentially moving target. A new path is repetitively recomputed and acceleration orthogonal to the path is applied to minimize heading error and thereby to converge on the target. The gain of the control function is partly proportional to heading error, but the gain is reduced approaching the point of convergence. In this way, the guidance control is more responsive to actual variance of the true heading error and is less responsive to random error in sensing the target heading, which random error would otherwise increase in its contribution to corrective guidance movements approaching the point of intersection.
摘要翻译：提供导弹或射弹及相关引导控制以控制与潜在移动目标的交点的路径。重复地重新计算新路径，并应用与路径正交的加速度，以最小化航向误差，从而收敛于目标。控制功能的增益部分与航向误差成比例，但增益减小接近收敛点。以这种方式，引导控制对真正方向误差的实际方差更有反应，并且对感测目标航向的随机误差的响应较小，随机误差对其接近交点的修正引导运动的贡献将增加。

7. 发明申请

US20090173820A1 GUIDANCE SYSTEM WITH VARYING ERROR CORRECTION GAIN 有权
标题翻译：指导系统具有变化的错误校正增益
公开(公告)号：US20090173820A1
公开(公告)日：2009-07-09
申请号：US11968705
申请日：2008-01-03
申请人： Gregory F. Bock
发明人： Gregory F. Bock
IPC分类号： F41G7/20 , F42B15/01
CPC分类号： F42B15/01 , F41G7/22 , G05D1/12
摘要： A guided missile or projectile and associated guidance control are provided to control a path to a point of intersection with a potentially moving target. A new path is repetitively recomputed and acceleration orthogonal to the path is applied to minimize heading error and thereby to converge on the target. The gain of the control function is partly proportional to heading error, but the gain is reduced approaching the point of convergence. In this way, the guidance control is more responsive to actual variance of the true heading error and is less responsive to random error in sensing the target heading, which random error would otherwise increase in its contribution to corrective guidance movements approaching the point of intersection.
摘要翻译：提供导弹或射弹及相关引导控制以控制与潜在移动目标的交点的路径。重复地重新计算新路径，并应用与路径正交的加速度，以最小化航向误差，从而收敛于目标。控制功能的增益部分与航向误差成比例，但增益减小接近收敛点。以这种方式，引导控制对真正方向误差的实际方差更有反应，并且对感测目标航向的随机误差的响应较小，随机误差对其接近交点的修正引导运动的贡献将增加。

8. 发明授权

US06473747B1 Neural network trajectory command controller 失效
标题翻译：神经网络轨迹指令控制器
公开(公告)号：US06473747B1
公开(公告)日：2002-10-29
申请号：US09004947
申请日：1998-01-09
申请人： James E. Biggers , Kevin P. Finn , Homer H. Schwartz, II , Richard A. McClain, Jr.
发明人： James E. Biggers , Kevin P. Finn , Homer H. Schwartz, II , Richard A. McClain, Jr.
IPC分类号： G06N302
CPC分类号： F41G7/22
摘要： An apparatus and method for controlling trajectory of an object (47) to a first predetermined position. The apparatus has an input layer (22) having nodes (22a-22f) for receiving input data indicative of the first predetermined position. First weighted connections (28) are connected to the nodes of the input layer (22). Each of the first weighted connections (28) have a coefficient for weighting the input data. An output layer (26) having nodes (26a-26e) connected to the first weighted connections (28) determines trajectory data based upon the first weighted input data. The trajectory of the object is controlled based upon the determined trajectory data.
摘要翻译：一种用于将物体（47）的轨迹控制到第一预定位置的装置和方法。该装置具有输入层（22），其具有用于接收表示第一预定位置的输入数据的节点（22a-22f）。第一加权连接（28）连接到输入层（22）的节点。第一加权连接（28）中的每一个具有用于对输入数据进行加权的系数。具有连接到第一加权连接（28）的节点（26a-26e）的输出层（26）基于第一加权输入数据确定轨迹数据。基于确定的轨迹数据来控制物体的轨迹。

9. 发明申请

US20020083027A1 Neural network trajectory command controller 有权
公开(公告)号：US20020083027A1
公开(公告)日：2002-06-27
申请号：US09789983
申请日：2001-02-21
发明人： James E. Biggers , Kevin P. Finn , Homer H. Schwartz II , Richard A. McClain JR.
IPC分类号： G06F015/18
CPC分类号： F41G7/22
摘要： An apparatus and method for controlling trajectory of an object (47) to a first predetermined position. The apparatus has an input layer (22) having nodes (22a-22f) for receiving input data indicative of the first predetermined position. First weighted connections (28) are connected to the nodes of the input layer (22). Each of the first weighted connections (28) have a coefficient for weighting the input data. An output layer (26) having nodes (26a-26e) connected to the first weighted connections (28) determines trajectory data based upon the first weighted input data. The trajectory of the object is controlled based upon the determined trajectory data.

10. 发明授权

US5660355A Angle only range estimator for homing missile 失效
标题翻译：用于归位导弹的角度范围估计器
公开(公告)号：US5660355A
公开(公告)日：1997-08-26
申请号：US652885
申请日：1996-05-23
申请人： Walter K. Waymeyer
发明人： Walter K. Waymeyer
IPC分类号： F41G7/22 , G05D1/12 , F42B15/01
CPC分类号： F41G7/22 , G05D1/12
摘要： Missile motion information from an inertial measurement set and the angle-to-target information from a seeker/sensor is used to estimate range and/or time to go on a homing missile without a direct measurement of range or range rate. Up to six comparisons of spectrally matched linear and angular measurements, corrected by target state estimates and analytical coupling terms, are used to determine the error in the range estimate. A nonlinear sorting and filtering procedure rejects the unusable error sources among the six potential error sources, and thresholds against too little information. The stability margin in the missile guidance loop is used as a sensor indicator for excessive estimated range.
摘要翻译：使用来自惯性测量装置的导弹运动信息和来自探测器/传感器的角度到目标信息来估计在导弹上的范围和/或时间，而无需直接测量范围或范围速率。通过目标状态估计和分析耦合项校正的频谱匹配的线性和角度测量多达六次比较，用于确定范围估计中的误差。非线性排序和过滤程序拒绝六个潜在错误源中不可用的错误源，以及对太少信息的阈值。导弹引导回路中的稳定裕度用作过度估计范围的传感器指示器。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式