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1. 发明公开

EP4010247A1 ATTITUDE DETERMINATION BY PULSE BEACON AND LOW COST INERTIAL MEASURING UNIT 审中-实审
公开(公告)号：EP4010247A1
公开(公告)日：2022-06-15
申请号：EP20849796.6
申请日：2020-08-06
申请人： BAE SYSTEMS Information and Electronic Systems Integration, Inc.
发明人： CHOINIERE, Michael, J. , BATCHELDER, Jason, H. , CHROBAK, Matthew, F.
IPC分类号： B64C39/02 , F42B15/01 , G01S19/53 , F41G7/36

2. 发明公开

EP3205973A1 A MISSILE FOR USE IN A LASER BEAM RIDING MISSILE GUIDANCE SYSTEM 有权转让
标题翻译：一种用于激光束导引头导引系统的导弹
公开(公告)号：EP3205973A1
公开(公告)日：2017-08-16
申请号：EP17154263.2
申请日：2017-02-01
申请人： Thales Holdings UK Plc
发明人： Mallon, Paddy , McConnell, George
IPC分类号： F41G7/26 , F41G7/22 , F41G7/00 , F41G7/36
CPC分类号： F41G7/26 , F41G7/008 , F41G7/226 , F41G7/2293 , F41G7/36
摘要： A method for aligning a missile with a target in a laser beam riding missile guidance system, the system including a laser transmitter for generating and projecting a laser information field towards the target and an optical sight for aiming the laser beam towards the target, the method comprising: determining a point in the laser information field with which the missile is currently aligned; determining a distance of the target from the missile; determining an angular displacement between the missile's current direction of travel and the direction in which the target lies from the missile; determining, based on said distance and angular displacement, a new point in the laser information field with which the missile should be aligned to reach the target; and controlling missile guidance systems on board the missile to bring the missile into alignment with the new point in the laser information field.
摘要翻译：一种用于在激光束导引引导系统中将导弹与目标对准的方法，所述系统包括用于产生激光信息场并将激光信息场投射到目标的激光发射器和用于将激光束瞄准目标的光学瞄准器，所述方法包括：确定导弹当前对准的激光信息字段中的点; 确定目标距导弹的距离; 确定导弹的当前行进方向与目标与导弹相对的方向之间的角位移; 基于所述距离和角位移确定激光信息字段中与导弹应该对齐以达到目标的新点; 并控制导弹上的导弹制导系统，使导弹与激光信息领域的新点对齐。

3. 发明授权

EP2060873B1 Verfahren zur Stützung der Trägheitsnavigation eines Flugkörpers 有权转让
标题翻译： Verfahren zurStützungderTrägheitsnavigationeinesFlugkörpers
公开(公告)号：EP2060873B1
公开(公告)日：2016-03-30
申请号：EP08019575.3
申请日：2008-11-08
申请人： MBDA Deutschland GmbH
发明人： Schweyer, Nikolaus , Holicki, Michael Dr. , Zoz, Jürgen Dr.
IPC分类号： G01C21/16 , G01C21/00 , F41G7/22 , F41G7/34 , F41G7/36 , G06K9/00 , G06T7/00
CPC分类号： G01C21/165 , F41G7/343 , F41G7/36 , G01C21/005 , G06K9/00201 , G06T7/74 , G06T2207/30212

4. 发明授权

EP2163844B1 Vehicle for aerial delivery of fire retardant 失效
标题翻译：该车为阻燃剂空运
公开(公告)号：EP2163844B1
公开(公告)日：2015-08-12
申请号：EP09169980.1
申请日：2009-09-10
申请人： Lonestar Inventions LP
发明人： Akcasu, Osman Ersed
IPC分类号： F41G7/30 , F41G7/36 , F41G7/34 , B64D1/16 , F42B12/36 , F42B12/50 , B64C39/02 , A62C3/02 , A62C99/00 , F42B15/10
CPC分类号： F41G7/30 , A62C3/025 , A62C99/009 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/128 , B64C2201/141 , B64C2201/145 , B64D1/16 , F41G7/346 , F41G7/36 , F42B12/36 , F42B12/50 , F42B15/105

5. 发明公开

EP2236975A3 Verfahren zum Abkoppeln eines Flugkörpers von einem Trägerluftfahrzeug 有权转让
标题翻译：一种用于从载机脱开导弹方法
公开(公告)号：EP2236975A3
公开(公告)日：2013-11-13
申请号：EP10003403.2
申请日：2010-03-30
申请人： MBDA Deutschland GmbH
发明人： Grabmeier, Michael
IPC分类号： F41G7/36 , F41F3/06 , B64D1/04
CPC分类号： B64D1/04 , F41F3/06
摘要： Ein Verfahren zum Abkoppeln eines Flugkörpers von einem Trägerluftfahrzeug, wobei der Flugkörper an einer Unterseite des Trägerluftfahrzeugs mittels einer Abkoppelvorrichtung lösbar angebracht ist, zeichnet sich dadurch aus, dass vor dem Abkoppeln des Flugkörpers vom Trägerluftfahrzeug aerodynamische Steuerflächen des Flugkörpers um einen vorgegebenen Winkel in eine Position ausgelenkt werden, in der die anströmende Luft ein die Nase des Flugkörpers nach unten drehendes Nickmoment erzeugt.

6. 发明公开

EP2163844A2 Vehicle for aerial delivery of fire retardant 失效
标题翻译： Fahrzeug zur Luftfracht eines Flammhemmers
公开(公告)号：EP2163844A2
公开(公告)日：2010-03-17
申请号：EP09169980.1
申请日：2009-09-10
申请人： Lonestar Inventions LP
发明人： Akcasu, Osman Ersed
IPC分类号： F41G7/34 , F41G7/30 , F41G7/36
CPC分类号： F41G7/30 , A62C3/025 , A62C99/009 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/128 , B64C2201/141 , B64C2201/145 , B64D1/16 , F41G7/346 , F41G7/36 , F42B12/36 , F42B12/50 , F42B15/105
摘要： A guided fire-retardant-containing bomb comprises a container with retractable wings, tail and elevators having the form factor of a conventional release vehicle, where the control surfaces are coupled via a controller to a GPS with inertial guidance control and an ability to receive external instructions, and a charge core to disintegrate and disperse the fire retardant or water.
摘要翻译：导向阻燃弹的炸弹包括具有伸缩翼的容器，具有常规释放车辆的形状因子的尾部和电梯，其中控制表面通过控制器耦合到具有惯性引导控制的GPS并具有接收外部能力说明书和电荷核心，以分解和分散阻燃剂或水。

7. 发明公开

EP0589645A1 Relative guidance using the global positioning system 失效
标题翻译：相对Lenkung手套GPS。
公开(公告)号：EP0589645A1
公开(公告)日：1994-03-30
申请号：EP93307391.8
申请日：1993-09-20
申请人： Hughes Aircraft Company
发明人： Youhanaie, Mark
IPC分类号： F41G7/36
CPC分类号： F41G7/346
摘要： A method for guiding a vehicle (30) to a target (28) includes furnishing a first vehicle (20) having a first global positioning system (GPS) receiver (24) fixed to receive global positioning signals from a selected constellation (46) of satellites in orbit above the earth and the second vehicle (30) having a second GPS receiver (32) fixed to receive global positioning signals from the same selected constellation (46) of GPS satellites. The first vehicle (20) locates the target (28) with an onboard sensor (26) and converts the location of the target (28) to the frame of reference of the selected constellation (46) of satellites of the GPS. The first vehicle (20) communicates this target position and the available set of GPS satellites to a navigation system of the second vehicle (30). The second vehicle (30) proceeds to the target location provided from the first vehicle (20) in the frame of reference of the GPS under control of its navigation system using the positioning signal derived from the second GPS receiver (32) fixed to receive positioning signals from the selected constellation (46) of satellites. In these operations, the second vehicle (30) remains within a sufficiently small operating distance of the position of the first vehicle (20) that variations in systematic bias errors between the first GPS receiver (24) and the second GPS receiver (32) are negligible.
摘要翻译：一种用于将车辆（30）引导到目标（28）的方法包括提供具有固定的第一全球定位系统（GPS）接收器（24）的第一车辆（20），以从所选择的星座（46）接收全球定位信号卫星在地球上轨道上，第二车辆（30）具有固定的第二GPS接收机（32），用于接收来自GPS卫星的相同选定星座（46）的全球定位信号。第一车辆（20）利用车载传感器（26）将目标（28）定位，并将目标（28）的位置转换成所选择的GPS星座（46）的参考系。第一车辆（20）将该目标位置和可用的GPS卫星组传送到第二车辆（30）的导航系统。第二车辆（30）使用从第二GPS接收器（32）导出的定位信号在其导航系统的控制下，在GPS的参照系中从第一车辆（20）提供的目标位置进行固定以接收定位来自所选星座（46）卫星的信号。在这些操作中，第二车辆（30）保持在第一车辆（20）的位置的足够小的操作距离内，第一GPS接收器（24）和第二GPS接收器（32）之间的系统偏置误差的变化是微不足道。

8. 发明公开

EP3407023A1 INERTIAL NAVIGATION SYSTEM 有权
公开(公告)号：EP3407023A1
公开(公告)日：2018-11-28
申请号：EP18173352.8
申请日：2018-05-18
申请人： Atlantic Inertial Systems Limited
发明人： FAULKNER, Nicholas Mark , SHEARD, John Keith
IPC分类号： G01C25/00 , G01C21/16 , G05D1/10 , F41G7/36
摘要： An inertial measurement system for a spinning projectile comprising: a first, roll gyro with an axis oriented substantially parallel to the spin axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system; a controller, arranged to: compute a current projectile attitude from the outputs of the first, second and third gyros, the computed attitude comprising a roll angle, a pitch angle and a yaw angle; operate a Kalman filter that receives a plurality of measurement inputs including at least the roll angle, pitch angle and yaw angle and that outputs at least a roll angle error; initialise the Kalman filter with a roll angle error uncertainty representative of a substantially unknown roll angle; generate at least one pseudo-measurement from stored expected flight data, the or each pseudo-measurement corresponding to an expected measurement input of the Kalman filter; provide said pseudo-measurements) to the corresponding measurement input of the Kalman filter; and apply the roll angle error from the Kalman filter as a correction to the roll angle; wherein the Kalman filter is arranged to calculate the roll angle error as a function of the pseudo-measurement(s). This process allows navigation approach in which integrated navigation is initialised immediately after power-up, even though the roll angle is unknown or only known to a very coarse degree. The navigation Kalman filter configured with this pseudo-measurement update process allows reliable and rapid convergence to an accurate navigation solution without the need for a discrete upfinding process as it is not reliant on any knowledge of the initial roll angle.

9. 发明公开

EP3213034A1 INERTIAL NAVIGATION SYSTEM WITH COMPENSATION OF ROLL SCALE FACTOR ERROR 有权
标题翻译：具有卷积因子误差补偿的惯性导航系统
公开(公告)号：EP3213034A1
公开(公告)日：2017-09-06
申请号：EP15790207.3
申请日：2015-10-27
申请人： Atlantic Inertial Systems Limited
发明人： SHEARD, John Keith , FAULKNER, Nicholas Mark
IPC分类号： G01C21/16 , G01C25/00 , F41G7/36 , F42B15/01 , G05D1/10
CPC分类号： G01C21/16 , F41G7/36 , F42B15/01 , G01C25/005
摘要： An inertial measurement system (200) for a longitudinal projectile, comprising a first, roll gyro to be oriented substantially parallel to the longitudinal axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system. The system further comprises a controller (225, 250), arranged: —to compute a current projectile attitude from the outputs of the first, second and third gyros, the computed attitude comprising a roll angle, a pitch angle and a yaw angle; —for at least two time points, to compare the computed pitch and yaw angles with expected values for the pitch and yaw angles; —for each of said at least two time points, to calculate a roll angle error based on the difference between the computed pitch and yaw angles and the expected pitch and yaw angles; —to calculate a roll angle error difference between said at least two time points; —to calculate the total roll angle subtended between said at least two time points; —to calculate a roll angle scale factor error based on said computed roll angle error difference and said total subtended roll angle and apply the calculated roll angle scale factor error to the output of the roll gyro.
摘要翻译：一种用于纵向射弹的惯性测量系统，包括：平行于射弹纵轴取向的第一滚转陀螺仪和相对于滚转陀螺仪设置的第二和第三陀螺仪，以限定三维坐标系统。由陀螺仪确定包括滚转角，俯仰角和偏航角的当前射弹姿态。对于至少两个时间点，将所确定的俯仰角和偏航角与期望值进行比较，并且基于所确定的和期望的俯仰角和偏航角之间的差来确定侧倾角误差。在这两个时间点之间计算横滚角误差差和总横摇角。基于所述侧倾角误差差和总对向侧倾角确定侧倾角比例因子误差，并将其应用于侧倾陀螺仪的输出。这提供了即使在发射后立即在高滚动速率阶段期间改进了滚动轴速率陀螺仪比例因子的校准。

10. 发明公开

EP2594890A1 Ratio-metric horizon sensing using an array of thermopiles 有权
标题翻译： Horizontsensor mit einer Anordnung vonThermosäulen
公开(公告)号：EP2594890A1
公开(公告)日：2013-05-22
申请号：EP12193042.4
申请日：2012-11-16
申请人： Simmonds Precision Products, Inc.
发明人： Durkee, Scott Robert
IPC分类号： F41G7/36 , G01S3/783 , F41G7/34 , F42B15/01
CPC分类号： G01S3/783 , F41G7/346 , F41G7/36 , F42B15/01
摘要： An example method includes receiving output voltage data from an array of at least four thermopiles placed around the circumference of a projectile such that for any rotation of the projectile during flight thereof, at least a pair of the thermopile having upwardly-facing fields of view referenced to the earth-fixed coordinate system. The method includes determining the pair of upwardly-facing thermopiles based on the output voltage data from the array, with the respective pair of thermopiles including a thermopile p and next adjacent thermopile p + 1. The method includes determining a ratio of the output voltage data from thermopiles p and p + 1, and applying the ratio to a function associating, for any pair of thermopiles n and n + 1, a ratio of output voltage data from thermopiles n and n + 1, and a roll angle θ n of thermopile n referenced to the earth-fixed coordinate system.
摘要翻译：一个示例性方法包括从围绕射弹圆周放置的至少四个热电堆的阵列接收输出电压数据，使得对于抛射体在其飞行期间的任何旋转，至少一对具有向上的视场参考的热电堆到地球固定坐标系。该方法包括基于来自阵列的输出电压数据确定一对向上的热电堆，相应的一对热电堆包括热电堆p和下一个相邻的热电堆p + 1。该方法包括确定输出电压数据从热电堆p和p + 1，并将该比率应用于与任何一对热电堆n和n + 1相关联的功能，来自热电堆n和n + 1的输出电压数据与热电堆的滚动角度¸n n参考地固定坐标系。

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