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61. 发明申请

WO2018140124A2 AUTOMATED DETERMINATION OF ROCKET CONFIGURATION 审中-公开
公开(公告)号：WO2018140124A2
公开(公告)日：2018-08-02
申请号：PCT/US2017/062545
申请日：2017-11-20
申请人： BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION INC.
发明人： SCHORR, David, J. , DAMIANO, Matthew , STEENSON, James, H.
IPC分类号： F42B15/01 , G06F17/50
摘要： Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.

62. 发明申请

WO2014058506A3 METHODS AND APPARATUSES FOR AUTONOMOUS FLIGHT TERMINATION 审中-公开
标题翻译：用于自动飞行终止的方法和设备
公开(公告)号：WO2014058506A3
公开(公告)日：2014-08-28
申请号：PCT/US2013051615
申请日：2013-07-23
申请人： ALLIANT TECHSYSTEMS INC
发明人： PAPADOPOULOS GEORGE B , DEVRIES DEREK R , THOMAS STEVEN W , VAN DIXHORN TIMOTHY J , WEIGEL CHARLES L , DEDON CHARLES L
IPC分类号： G05D1/00 , B64G1/00 , B64G1/52 , F41G7/34 , F42B15/01
CPC分类号： F42B10/48 , B64G1/002 , B64G1/52
摘要： Embodiments include a flight safety assembly onboard an aerial vehicle, which includes a first sensor configured to sense first information related to flight of the aerial vehicle and a second sensor configured to sense second information related to the flight of the aerial vehicle. A sensor input is adapted to receive third information related to the flight of the aerial vehicle. A processor is operably coupled to the first sensor, the second sensor, and the sensor input. The processor is configured to determine three independent instantaneous impact points for the aerial vehicle by independently analyzing each of the first information, the second information and the third information. The processor is also configured to generate three independent onboard flight termination indicators for each of the three independent instantaneous impact points that intersects with a region to be protected.
摘要翻译：实施例包括机载在飞行器上的飞行安全组件，其包括被配置为感测与飞行器的飞行有关的第一信息的第一传感器和被配置为感测与飞行器的飞行有关的第二信息的第二传感器。传感器输入适于接收与飞行器的飞行有关的第三信息。处理器可操作地耦合到第一传感器，第二传感器和传感器输入。处理器被配置成通过独立分析第一信息，第二信息和第三信息中的每一个来确定用于飞行器的三个独立瞬时撞击点。处理器还被配置为针对与要保护的区域相交的三个独立瞬时冲击点中的每一个生成三个独立的机载飞行终止指示符。

63. 发明申请

WO2014035525A3 ACTIVE COOLING OF HIGH SPEED SEEKER MISSILE DOMES AND RADOMES 审中-公开
公开(公告)号：WO2014035525A3
公开(公告)日：2014-03-06
申请号：PCT/US2013/045426
申请日：2013-06-12
申请人： INTEGRAL LASER SOLUTIONS, LLC. , THE CURATORS OF THE UNIVERSITY OF MISSOURI
发明人： SCHLIE, LaVerne Arthur , MA, Hongbin
IPC分类号： F42B15/34 , F42B15/01 , F42B12/76 , B64C1/38
摘要： A thermal management system and method for active cooling of high speed seeker missile domes or radomes comprising bonding to an IR dome or RF radome a heat pipe system having effective thermal conductivity of 10 - 20,000 W/m*K and comprising one or more mechanically controlled oscillating heat pipes, employing supporting integrating structure including a surface bonded to the IR dome or RF radome that matches the coefficient of thermal expansion the dome or radome material and that of said one or more mechanically controlled oscillating heat pipes, and operating the heat pipe system to cool the IR dome or RF radome while the missile is in flight.

64. 发明申请

WO2013011510A4 MUNITION GUIDANCE SYSTEM AND METHOD OF ASSEMBLING THE SAME 审中-公开
标题翻译： MUNITION GUIDANCE SYSTEM及其组装方法
公开(公告)号：WO2013011510A4
公开(公告)日：2013-03-07
申请号：PCT/IL2012050255
申请日：2012-07-18
申请人： ELBIT SYSTEMS LTD , ELKAYAM AMI , AZAR ZEEV
发明人： ELKAYAM AMI , AZAR ZEEV
IPC分类号： F42B15/01
CPC分类号： F41G7/22 , F41G7/20 , F42B10/64 , F42B15/01 , F42B33/00
摘要： A munition guidance system is disclosed. The system comprises a generally tubular enclosure, having an internal cavity adapted for receiving a munition, wherein an outer diameter of the enclosure is at most the largest outer diameter of the munition; and a processing and control unit enclosed within the enclosure and being configured for controlling guidance wings so as to maneuver the munition while flying.
摘要翻译：披露军火指导系统。该系统包括大致管状的外壳，该外壳具有适于接纳弹药的内腔，其中外壳的外径至多是弹药的最大外径; 以及封闭在所述外壳内的处理和控制单元，所述处理和控制单元被配置为控制引导翼以便在飞行时操纵弹药。

65. 发明申请

WO2013028301A1 ROLLING VEHICLE HAVING COLLAR WITH PASSIVELY CONTROLLED AILERONS 审中-公开
标题翻译：带有常规控制的航空器的滚动车
公开(公告)号：WO2013028301A1
公开(公告)日：2013-02-28
申请号：PCT/US2012/047833
申请日：2012-07-23
申请人： RAYTHEON COMPANY , GESWENDER, Chris, E. , VESTY, Paul , FROST, Geoffrey, W. , MORGAN, Bruce, E.
发明人： GESWENDER, Chris, E. , VESTY, Paul , FROST, Geoffrey, W. , MORGAN, Bruce, E.
IPC分类号： F42B10/64 , F42B15/01
CPC分类号： F42B10/64 , F42B15/01
摘要： A spinning, rolling, or roll-stabilized vehicle, such as a projectile (10), includes a fuselage (12) that rotates about its longitudinal axis (spins) during flight. A collar (24) is positionable relative to the fuselage (12) to steer the projectile (10), with the collar (24) having ailerons (28) to provide a roll force to position the collar (24). The collar (24) also has elevators (26) to provide lateral force to steer the projectile (10). The positioning of the collar (24) may be accomplished by moderating the roll force of the ailerons (28) to hold the position of the collar (24) substantially constant with regard to a longitudinal axis of the projectile (10). The ailerons (28) passively change angle of attack with changes in the dynamic pressure of the projectile (10).
摘要翻译：诸如射弹（10）的旋转，滚动或滚动稳定的车辆包括在飞行期间围绕其纵向轴线（旋转）旋转的机身（12）。套环（24）可相对于机身（12）定位以引导射弹（10），套环（24）具有副翼（28）以提供滚动力以定位套环（24）。轴环（24）还具有电梯（26），以提供侧向力来引导射弹（10）。套环（24）的定位可以通过调节副翼（28）的滚动力来保持套环（24）的位置相对于射弹（10）的纵向轴线基本恒定来实现。副翼（28）被动地改变了射弹的动态压力（10）。

66. 发明申请

WO2011152901A3 SPOT LEADING TARGET LASER GUIDANCE FOR ENGAGING MOVING TARGETS 审中-公开
标题翻译： SPOT引导目标激光瞄准移动目标
公开(公告)号：WO2011152901A3
公开(公告)日：2012-02-16
申请号：PCT/US2011026054
申请日：2011-02-24
申请人： LOCKHEED CORP , GLAROS LOUIS N , EDDINS WILLIAM B , GAYLORD CHARLES , KINCHELOE MICHAEL
发明人： GLAROS LOUIS N , EDDINS WILLIAM B , GAYLORD CHARLES , KINCHELOE MICHAEL
IPC分类号： F41G7/26 , F41G7/24 , F42B15/01
CPC分类号： F42B15/01 , F41G3/145 , F41G7/226 , F41G7/2293
摘要： A laser lead designator (320) for guiding a laser guided weapon (LGW) to strike a moving target includes a laser source (321) for providing a laser beam (322) and a controller (328) coupled to receive a position and a velocity of the moving target from a target tracker (310). Using a laser lead table (330) as a look-up table, the controller provides a control signal (323) for pointing the laser beam a specified lead distance ahead of the position of the moving target to position a laser spot on a ground location ahead of the moving target. The lead distance compensates for an impact shortfall value that is a function of at least one shortfall parameter including a speed of the moving target so that the LGW shortfalls the laser spot on the moving target. The laser designator is separate from the LGW.
摘要翻译：用于引导激光制导武器（LGW）撞击移动目标的激光引线指示器（320）包括用于提供激光束（322）的激光源（321）和耦合以接收位置和速度的目标跟踪器（310）。使用激光引导台（330）作为查找表，控制器提供控制信号（323），用于将激光束指向移动目标位置之前的指定前导距离，以将激光点定位在地面位置领先于移动目标。引导距离补偿了影响不足值，这是至少一个包括移动目标的速度的缺陷参数的函数，以致LGW将移动目标上的激光点不足。激光指示器与LGW分开。

67. 发明申请

WO2012005786A2 AUTOMATIC RE-INITIALIZATION OF RESONANT SENSORS IN ROCKET AND MISSILE GUIDANCE SYSTEMS 审中-公开
标题翻译：谐振传感器自动重新起动在轨道和导向系统
公开(公告)号：WO2012005786A2
公开(公告)日：2012-01-12
申请号：PCT/US2011/031657
申请日：2011-04-08
申请人： BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION INC. , JANIAK, Derek, P. , STEENSON, James, H. Jr. , SCHORR, David , BARTLETT, Stephen, William
发明人： JANIAK, Derek, P. , STEENSON, James, H. Jr. , SCHORR, David , BARTLETT, Stephen, William
IPC分类号： F42B15/08 , G01L9/00 , F42B15/01
CPC分类号： F42B15/01 , B64G1/36 , G01L27/007
摘要： An apparatus and method improves the fault tolerance of a rocket or missile guidance system which includes a resonant sensor. When improper initialization is detected, the resonant sensor is reinitialized, repeatedly if necessary, until normal operation is achieved. Improper initialization is detected by comparing data from the guidance system with pre-specified physical limits to roll, pitch, yaw, and/or other features of the flight scenario. Embodiments can also detect a fault condition due to an error signal from a "Built-in-Test" (BIT) module. The initialization sequence initiated by the invention can be identical to the power-on sequence, or it can be a separate, reinitiating sequence. Subsequent resets are initiated as needed, for example until the burn of the rocket fuel and the associated vibrations have ceased and the resonant sensor has been successfully initialized.
摘要翻译：一种装置和方法提高了包括谐振传感器的火箭或导弹引导系统的容错性。当检测到不正确的初始化时，如果需要，可以重复初始化谐振传感器，直到达到正常工作。通过将来自引导系统的数据与预定的物理限制与飞行情景的滚动，俯仰，偏航和/或其他特征进行比较来检测不正确的初始化。实施例还可以检测来自“内置测试”（BIT）模块的错误信号的故障状况。由本发明启动的初始化序列可以与上电序列相同，或者可以是单独的再启动序列。随后的复位根据需要开始，例如直到火箭燃料的燃烧和相关联的振动已经停止并且谐振传感器已被成功初始化。

68. 发明申请

WO2011152901A2 SPOT LEADING TARGET LASER GUIDANCE FOR ENGAGING MOVING TARGETS 审中-公开
标题翻译： SPOT引导目标激光瞄准移动目标
公开(公告)号：WO2011152901A2
公开(公告)日：2011-12-08
申请号：PCT/US2011/026054
申请日：2011-02-24
申请人： LOCKHEED MARTIN CORPORATION , GLAROS, Louis N. , EDDINS, William B. , GAYLORD, Charles , KINCHELOE, Michael
发明人： GLAROS, Louis N. , EDDINS, William B. , GAYLORD, Charles , KINCHELOE, Michael
IPC分类号： F41G7/26 , F42B15/01 , F41G7/24
CPC分类号： F42B15/01 , F41G3/145 , F41G7/226 , F41G7/2293
摘要： A laser lead designator (320) for guiding a laser guided weapon (LGW) to strike a moving target includes a laser source (321) for providing a laser beam (322) and a controller (328) coupled to receive a position and a velocity of the moving target from a target tracker (310). Using a laser lead table (330) as a look-up table, the controller provides a control signal (323) for pointing the laser beam a specified lead distance ahead of the position of the moving target to position a laser spot on a ground location ahead of the moving target. The lead distance compensates for an impact shortfall value that is a function of at least one shortfall parameter including a speed of the moving target so that the LGW shortfalls the laser spot on the moving target. The laser designator is separate from the LGW.
摘要翻译：用于引导激光制导武器（LGW）撞击移动目标的激光引线指示器（320）包括用于提供激光束（322）的激光源（321）和耦合以接收位置和速度的目标跟踪器（310）。使用激光引导台（330）作为查找表，控制器提供控制信号（323），用于将激光束指向移动目标位置之前的指定前导距离，以将激光点定位在地面位置领先于移动目标。引导距离补偿了影响不足值，这是至少一个包括移动目标的速度的缺陷参数的函数，从而使LGW在运动目标上缺少激光点。激光指示器与LGW分开。

69. 发明申请

WO2011059530A3 PASSIVE ELECTRO-OPTICAL TRACKER 审中-公开
标题翻译：被动式电光源追踪器
公开(公告)号：WO2011059530A3
公开(公告)日：2011-10-20
申请号：PCT/US2010035984
申请日：2010-05-24
申请人： LIGHT PRESCRIPTIONS INNOVATORS , AGUROK ILYA , FALICOFF WAQIDI
发明人： AGUROK ILYA , FALICOFF WAQIDI
IPC分类号： F41G7/20 , F41G3/14 , F41G7/26 , F42B15/01 , G01S19/18
CPC分类号： G06T7/246 , G06T2207/10016 , G06T2207/10048 , G06T2207/30212 , G06T2207/30241
摘要： A passive electro-optical tracker uses a two-band IR intensity ratio to discriminate high-speed projectiles and obtain a time-varying speed estimate from their time- varying temperature, as well as determining the trajectory back to the source of fire. In an omnidirectional system a hemispheric imager with an MWIR spectrum splitter forms two CCD images of the environment. Various methods are given to determine the azimuth and range of a projectile, both for clear atmospheric conditions and for nonhomogeneous atmospheric conditions. One approach uses the relative intensity of the image of the projectile on the pixels of a CCD camera to determine the azimuthal angle of trajectory with respect to the ground, and its range. A second uses a least squares optimization over multiple frames based on a triangle representation of the smeared image to yield a real-time trajectory estimate.
摘要翻译：无源电光跟踪器使用双频IR强度比来区分高速射弹，并根据它们的时变温度获得时变速度估计值，并确定回到火源的轨迹。在全方位系统中，带有MWIR光谱分离器的半球成像器形成两个环境的CCD图像。给出了各种方法来确定射弹的方位角和射程，无论是对于清晰的大气条件还是非均匀的大气条件。一种方法使用CCD相机像素上的抛射物图像的相对强度来确定轨迹相对于地面的方位角及其范围。第二个基于涂抹图像的三角形表示在多个帧上使用最小二乘法优化以产生实时轨迹估计。

70. 发明申请

WO2011037663A1 ROCKET GUIDANCE ADAPTER 审中-公开
标题翻译： ROCKET指导适配器
公开(公告)号：WO2011037663A1
公开(公告)日：2011-03-31
申请号：PCT/US2010/039070
申请日：2010-06-17
申请人： RAYTHEON COMPANY , MELLOR, Timothy, B. , BROGMUS, Eric , DUNN, George, E. , WILLEMS, Patrick , SEDIG, Mark, L.
发明人： MELLOR, Timothy, B. , BROGMUS, Eric , DUNN, George, E. , WILLEMS, Patrick , SEDIG, Mark, L.
IPC分类号： F42B15/01
CPC分类号： F42B15/01 , Y10T29/49826
摘要： A two-piece adapter (46,80) for mounting a guidance system (82) on unguided rockets allows for the existing designs and stores of unguided rockets to be retrofitted with guidance capability to provide a "guided rocket". The adapter provides the external mounting features (66,96) for mounting the guidance system and does so in a manner that transfers the steering loads of the guidance system to the rocket airframe and maintains the proper preloading and relationship of the fuze-to-warhead to detonate the warhead (42). The two- piece adapter comprises an inner adapter (46) and an outer adapter (80). The inner adapter is secured between the fuze (40) and warhead (42) without requiring modifications of either part and provides the external mounting feature (66). The outer adapter (80) is secured to the inner adapter (46) and effectively moves the external mounting feature (96) forward in front of the fuze (40) where the guidance system (82) is attached.
摘要翻译：用于将引导系统（82）安装在非导轨火箭上的两件式适配器（46,80）允许对具有引导能力的未导向火箭的现有设计和存储进行改装以提供“导向火箭”。适配器提供用于安装导向系统的外部安装特征（66,96），并以这样的方式将导向系统的转向载荷传递到火箭机身，并保持引信到弹头的适当预加载和关系引爆弹头（42）。两件式适配器包括内部适配器（46）和外部适配器（80）。内部适配器固定在引信（40）和弹头（42）之间，而不需要修改任何一个部件，并提供外部安装特征（66）。外部适配器（80）固定到内部适配器（46）上，并有效地将外部安装特征（96）向前移动到引导系统（82）附接的引信（40）的前方。

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