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1. 发明授权

US10141624B2 Method for dynamic heat sensing in hypersonic applications 有权
公开(公告)号：US10141624B2
公开(公告)日：2018-11-27
申请号：US15176700
申请日：2016-06-08
申请人： Raytheon Company
发明人： Glafkos K. Stratis , Anton Vanderwyst , Wayne L. Sunne , David G. Derrick
IPC分类号： H01Q1/02 , F42B10/46 , H01Q1/42 , H01Q1/28 , F42B15/34 , H01Q5/22 , H01Q1/00 , F42B15/00
摘要： A heat sensing system and method for dynamic heat sensing may be implemented in a flight vehicle having a main antenna configured for sending and/or receipt of signals. The system includes an auxiliary antenna system that is arranged within a radome of the flight vehicle for detecting temperatures around the exterior surface of the radome. The auxiliary antenna is configured for receiving and measuring infrared or optical energy. Using the measured energy, the system is configured to determine whether the detected temperature exceeds a predetermined temperature and rotating the vehicle to equalize heat around the vehicle when the current temperature exceeds the predetermined temperature.

2. 发明授权

US09777989B2 Launch system for a guided missile and a guided missile for such a launch system 有权
公开(公告)号：US09777989B2
公开(公告)日：2017-10-03
申请号：US15152261
申请日：2016-05-11
申请人： MBDA Deutschland GmbH
发明人： Stefan Lehmann , Jörg Lutzenberger
IPC分类号： F41F3/045 , F41A19/06 , F41A19/13 , F42B15/00
CPC分类号： F41F3/0455 , F41A19/06 , F41A19/13 , F41F3/045 , F42B15/00
摘要： The present embodiment relates to a guided missile launch system comprising a launch tube with a guided missile space for receiving a guided missile and with a cartridge space for receiving a blank cartridge, further comprising a handle piece mountable on the launch tube and separable from the launch tube, the handle piece having a striking pin system for firing the blank cartridge.

3. 发明授权

US09702670B2 Countermeasure flares 有权
公开(公告)号：US09702670B2
公开(公告)日：2017-07-11
申请号：US13971831
申请日：2013-08-20
申请人： Jahangir S Rastegar , Richard T Murray , Gretel Raibeck , Jay Poret , Brandon Andreola , Andrew Zimmer
发明人： Jahangir S Rastegar , Richard T Murray , Gretel Raibeck , Jay Poret , Brandon Andreola , Andrew Zimmer
IPC分类号： F42B4/26 , F41J2/00 , F41J2/02 , F42B10/14 , F42B10/16 , F42B10/26 , F42B15/00 , F42B15/10
CPC分类号： F42B4/26 , F41J2/00 , F41J2/02 , F42B10/14 , F42B10/16 , F42B10/26 , F42B15/00 , F42B15/10
摘要： Methods and devices for ejecting a grain assembly from a casing of a flare. Where a combustible material in the casing is ignited to eject the grain assembly and one or more of the following features are provided to the device: imparting a spin on the grain assembly after it is ejected from the casing, stabilizing a flight of the grain assembly or generating a thrust from an aft end of the grain assembly.

4. 发明授权

US09568280B1 Solid nose cone and related components 有权
标题翻译：固体鼻锥及相关成分
公开(公告)号：US09568280B1
公开(公告)日：2017-02-14
申请号：US14463217
申请日：2014-08-19
申请人： Lockheed Martin Corporation
发明人： Gary Paul Perryman , Bruno J. Evans , Thomas Hiromoto , Jillian L. Roettiger
IPC分类号： F41G7/26 , F41G7/22 , F42B15/01 , F42B12/02 , F41G7/00 , F42B15/00
CPC分类号： F41G7/2293 , F41G7/2246 , F41G7/2253 , F41G7/226 , F42B10/46 , F42B15/01 , G01S3/781 , G01S3/784
摘要： A solid nose cone and related components are disclosed. Embodiments include a front-end system for a laser-guided munition. The front-end system includes a solid nose cone that is optically transparent to electromagnetic radiation (EMR) of a particular wavelength. The solid nose cone is configured to pass EMR incident on the exterior surface to the trailing end. An optical relay adapter (ORA) has an EMR-receiving front face and an EMR-emitting rear face. The EMR-receiving front face is optically coupled to the trailing end, and the ORA is configured to relay the EMR from the EMR-receiving front face to the EMR-emitting rear face.
摘要翻译：公开了一种坚固的鼻锥和相关部件。实施例包括用于激光制导弹药的前端系统。前端系统包括对特定波长的电磁辐射（EMR）光学透明的固体鼻锥体。固体鼻锥构造成将入射到外表面的EMR传递到尾端。光学继电器适配器（ORA）具有EMR接收前面和EMR发射后面。 EMR接收前面光学地耦合到后端，并且ORA被配置为将EMR从EMR接收前面继续发送到EMR发射后面。

5. 发明授权

US09488422B2 Grenade and grenade launching apparatus 有权
标题翻译：手榴弹和手榴弹发射装置
公开(公告)号：US09488422B2
公开(公告)日：2016-11-08
申请号：US12976434
申请日：2010-12-22
申请人： Helmut Hammer , Axel Pfersmann
发明人： Helmut Hammer , Axel Pfersmann
IPC分类号： F42B15/00 , F41A1/08 , F42B30/10 , F42B5/10 , F42B15/04 , F42B10/06 , F42C19/08
CPC分类号： F41A1/08 , F42B5/10 , F42B10/06 , F42B15/04 , F42B30/10 , F42C19/0826
摘要： The present invention relates to a grenade that can be fired from a barrel, for recoilless firing. The barrel is open at both ends and is without any flow cross-section constrictions. The grenade is formed of a grenade base body which surrounds at least one explosive charge, and a flow cross-section reduction device for reducing the flow cross-section of the barrel. The device is arranged in the opposite direction to the firing direction X with respect to the grenade base body. The flow cross-section reduction device is connected to the grenade base body, separated from it, via a connecting device, and is connected to it such that it is stable during firing. A grenade launcher or shell firing apparatus has a grenade such as this, and the grenade firing apparatus has a barrel which is open at both ends and does not have any flow cross-section constrictions.
摘要翻译：本发明涉及一种能够从枪管中发射的手榴弹，用于无后坐力的射击。枪管在两端开放，没有任何流动横截面的收缩。手榴弹由围绕至少一个炸药的手榴弹基体形成，以及用于减小枪管的流动横截面的流动横截面减小装置。该装置相对于手榴弹基体在与发射方向X相反的方向上布置。流动横截面减小装置通过连接装置与手榴弹基体连接，与其分离，并与其连接，使其在点火期间稳定。手榴弹发射器或炮弹装置具有这样的手榴弹，并且手榴弹发射装置具有在两端敞开并且没有任何流动横截面收缩的枪管。

6. 发明授权

US09441929B2 Tactical missile and balance weight for said missile 有权
标题翻译：导弹的战术导弹和平衡重量
公开(公告)号：US09441929B2
公开(公告)日：2016-09-13
申请号：US14384836
申请日：2013-03-18
申请人： MBDA FRANCE
发明人： Patrick Barthelemy , Phillippe Dubois , Laurent Carton , Nicholas Sibillaud , Marc Ferrat , Frederic Paintendre
IPC分类号： F16F15/32 , F42B15/01 , F42B10/02 , F16F15/00 , F42B15/00
CPC分类号： F42B15/01 , F16F15/32 , F42B10/02
摘要： According to the invention, the balance weights of the missile are made from pellets whereof the particle size is at most equal to 1 mm which is enclosed in a closed package.
摘要翻译：根据本发明，导弹的平衡重是由粒径最大等于1mm的颗粒制成，封闭在封闭的包装中。

7. 发明授权

US09377279B2 Rocket cluster divert and attitude control system 有权
标题翻译：火箭群转移和姿态控制系统
公开(公告)号：US09377279B2
公开(公告)日：2016-06-28
申请号：US14258274
申请日：2014-04-22
申请人： Raytheon Company
发明人： Andrew B. Facciano , William G. Graves , Michael A. Barker , Michael S. Alkema , Jeffrey S. Larson
IPC分类号： F42B10/66 , F42B15/01 , F42B10/00 , F42B15/00
CPC分类号： F42B15/01 , F42B10/661 , F42B10/663
摘要： A flight vehicle includes a nose portion, a fuselage retaining structure aft of the nose portion, and an axial motor for expelling axial thrust along a longitudinal axis of the flight vehicle. Radial motors are coupled to the retaining structure and axisymmetrically arranged about the axial motor. Each radial motor is configured to expel radial thrust radially outwardly in respect to the flight vehicle. Roll thrusters are operatively coupled with the radial motors and coupled to the fuselage retaining structure. The roll thrusters are configured to provide a roll moment of the flight vehicle about a central longitudinal axis of the flight vehicle. Ejectors are operatively coupled to the radial motors, and a controller is operatively coupled to the radial motors and the ejectors. The controller is configured to selectively fire and selectively eject the radial motors to maintain relative centering of a center of gravity of the flight vehicle.
摘要翻译：飞行器车辆包括鼻部，机身保持结构在前部的后部，以及用于沿着飞行器车辆的纵向轴线排出轴向推力的轴向马达。径向电动机联接到保持结构并围绕轴向电动机轴对称布置。每个径向马达构造成相对于飞行器车辆径向向外排出径向推力。滚动推进器可操作地与径向马达耦合并联接到机身保持结构。滚动推进器被配置成围绕飞行器车辆的中心纵向轴线提供飞行车辆的滚动时刻。喷射器可操作地联接到径向马达，并且控制器可操作地联接到径向马达和喷射器。控制器被配置为选择性地起动并选择性地弹出径向马达以维持飞行器车辆的重心的相对定心。

8. 发明授权

US09366514B1 System, method and computer program product for providing for a course vector change of a multiple propulsion rocket propelled grenade 有权
标题翻译：用于提供多推进火箭推进榴弹的航向矢量变化的系统，方法和计算机程序产品
公开(公告)号：US09366514B1
公开(公告)日：2016-06-14
申请号：US14631108
申请日：2015-02-25
申请人： LOCKHEED MARTIN CORPORATION
发明人： Harry R. Barnard , Toby D. Thomas
IPC分类号： F41G7/22 , F42B15/01 , F41G3/14 , G05D1/12 , G05D1/08 , F41G7/20 , F41G7/00 , F42B15/00
CPC分类号： F42B15/01 , F41G7/20 , F41G7/22 , F41G7/226 , F41G7/2293 , F42B10/14 , F42B10/48 , F42B30/04 , G05D1/107
摘要： Embodiments relate to a projectile system, method and computer program product for controlling the flight of a projectile to make a course change by approximately 90°, greater than 90° or up to 90°. The projectile system comprises a gun-fired projectile having a body, at least one tail fin, a motor firing during a first flight phase and during a second flight phase and at least one controllable canard. The projectile system includes one or more processors configured to determine a turn maneuver profile to a target during the first flight phase, produce control signals to destabilize the body, create a pitch attitude change for the turn maneuver profile and effectuate a turn of the projectile in a direction corresponding to the turn maneuver profile during the first flight phase. The processors control the motor to start the second flight phase to the target after the turn.
摘要翻译：实施例涉及一种用于控制射弹飞行以使航向变化约90°，大于90°或高达90°的射弹系统，方法和计算机程序产品。射弹系统包括具有主体，至少一个尾鳍，在第一次飞行阶段期间和在第二次飞行阶段期间起动的电动机的喷枪射弹和至少一个可控制的挡板。射弹系统包括一个或多个处理器，其被配置为在第一飞行阶段期间确定目标的转弯机动轮廓，产生控制信号以使身体不稳定，为转弯机动轮廓创建俯仰姿态变化并且实现弹射转向在第一次飞行阶段期间对应于转向机动轮廓的方向。处理器控制电机在转弯后开始第二次飞行阶段到目标。

9. 发明授权

US09074858B2 Projectile-deployed countermeasure system 有权
标题翻译：弹药部署对策系统
公开(公告)号：US09074858B2
公开(公告)日：2015-07-07
申请号：US13682256
申请日：2012-11-20
申请人： The Boeing Company
发明人： Dennis Yee , Timothy L. Williams
IPC分类号： F42B15/10 , F42B12/56 , F41H11/02 , F41H13/00 , F41F3/04 , F42B15/00 , F42B15/01
CPC分类号： F42B12/56 , F41F3/04 , F41H11/02 , F41H13/0006 , F42B15/00 , F42B15/01
摘要： Systems and methods described herein provide for the protection of personnel within vehicles and structures from rocket-propelled grenades and other incoming threats. According to one aspect of the disclosure provided herein, a countermeasure system includes an interceptor vehicle configured to stow and launch an expandable countermeasure. The countermeasure may have a flexible body with attached deployment mechanisms that expand the flexible body into the path of an incoming threat to capture the threat.
摘要翻译：本文所述的系统和方法规定保护车辆和结构内的人员免受火箭榴弹和其他威胁。根据本文提供的本公开的一个方面，一种对策系统包括配置成收起并发起可展开对策的拦截器车。对策可能具有灵活的身体，其具有附接的部署机构，其将柔性身体扩展到进入的威胁的路径以捕获威胁。

10. 发明授权

US08933382B2 Guidance system and method for missile divert minimization 有权
标题翻译：导弹转移最小化指导系统和方法
公开(公告)号：US08933382B2
公开(公告)日：2015-01-13
申请号：US13076690
申请日：2011-03-31
申请人： Andrew E. Dolphin
发明人： Andrew E. Dolphin
IPC分类号： F42B15/01 , F41G9/00 , G05D1/10 , G05D1/12 , F42B15/00
CPC分类号： F42B15/01 , G05D1/107 , G05D1/12
摘要： A missile guidance system is configured to estimate a time to go, the time to go comprising an amount of time until a missile would reach a closest point of approach to a target. The guidance system is also configured to estimate a zero-effort miss distance along a zero-effort miss vector, the zero-effort miss distance comprising a distance by which the missile would miss the target if the missile performs no future maneuvers. The guidance system is also configured to determine a tolerance for the zero-effort miss distance, the tolerance being a function of the time to go. The guidance system is further configured to modify a course of the missile by adjusting an expenditure of propellant such that the estimated zero-effort miss distance in excess of the tolerance is removed from future consideration.
摘要翻译：导弹指导系统被配置为估计一段时间，即时间到达导弹到达最接近目标点的时间量。引导系统还被配置为估计零努力缺失向量的零努力缺失距离，零努力缺失距离包括如果导弹不执行将来的操纵，导弹将错过目标的距离。引导系统还被配置为确定零努力缺失距离的公差，该公差是待去时间的函数。引导系统还被配置为通过调整推进剂的支出来修改导弹的航向，使得超过公差的估计零功率缺失距离从将来考虑中被去除。

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