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    • 3. 发明申请
    • GUIDED KINETIC PENETRATOR
    • 指导动力穿孔器
    • WO2006107530A2
    • 2006-10-12
    • PCT/US2006009105
    • 2006-03-14
    • RAYTHEON COSCHNEIDER ARTHUR
    • SCHNEIDER ARTHUR
    • F42B10/00
    • F41G7/301F42B10/64F42B12/06F42B15/01
    • The disclosed system, device and method for guiding a hypersonic kinetic penetrator projectile (300) generally includes a kinetic penetrator body (110, 230) and a slip-over electronic guidance unit (120, 220), where the kinetic penetrator body slidably mounts through the slip-over electronic guidance unit. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve accuracy and control of a hypersonic projectile. Exemplary embodiments of the present invention generally provide multi-use slip-over electronic guidance units for hypersonic kinetic penetrator projectiles in 105 mm and 120 mm munition rounds, surface-to-surface missiles, and air-to-surface missiles.
    • 用于引导超音速动力穿透器射弹(300)的所公开的系统,装置和方法通常包括动力穿透体(110,230)和滑动式电子引导单元(120,220),其中动力穿透体可滑动地安装穿过 滑动电子引导单元。 公开的特征和规格可以被不同地控制,适应或以其他方式任意地修改以提高超音速射弹的精度和控制。 本发明的示例性实施例通常提供用于105mm和120mm弹药弹,地对地导弹和空对地导弹的超音速动力穿透器射弹的多用途滑移电子引导单元。
    • 4. 发明申请
    • ACTIVE PROTECTION METHOD AND SYSTEM
    • 主动保护方法和系统
    • WO2008035338A2
    • 2008-03-27
    • PCT/IL2007001153
    • 2007-09-20
    • ELTA SYSTEMS LTDLONGMAN DAVIDTZLIL JACOB
    • LONGMAN DAVIDTZLIL JACOB
    • F41G5/08F41G7/22F41G7/30
    • F41G7/301F41G5/08F41G7/224
    • There is provided an active protection system and an active protection method preferably for airborne platforms. According to an embodiment of the invention, the active protection system is mounted onboard a platform for protecting the platform, and comprises a radar system configured for generating output data including threat output data corresponding to a velocity, a range, and an angle of the threat with respect to the platform in an airspace around the platform, the output data being useful for detecting, identifying and tracking of at least one threat approaching the platform; a countermeasure system capable of launching at least one non-fragmentation interceptor projectile in response to receiving a control command; and a control unit configured for receiving the output data from the radar system and for generating the control command and transmitting the control command to the at least one non-fragmentation interceptor projectile, thereby enabling countering the threat.
    • 提供了一种用于机载平台的主动保护系统和主动保护方法。 根据本发明的一个实施例,主动保护系统被安装在用于保护平台的平台上,并且包括雷达系统,该雷达系统被配置用于生成包括与威胁的速度,范围和角度相对应的威胁输出数据的输出数据 相对于平台周围空域中的平台,输出数据对于检测,识别和跟踪接近平台的至少一个威胁是有用的; 响应于接收控制命令而能够发射至少一个非碎片拦截弹子弹的对抗系统; 以及控制单元,其被配置为接收来自雷达系统的输出数据并且用于生成控制命令并将控制命令发送到至少一个非碎片拦截弹子体,从而能够对抗威胁。
    • 6. 发明申请
    • METHOD AND GUIDANCE SYSTEM FOR GUIDING A MISSILE
    • 用于引导故障的方法和指导系统
    • WO01014820A1
    • 2001-03-01
    • PCT/SE2000/001557
    • 2000-08-09
    • F41G7/30F41G7/00F41G3/14F41G7/24F41G7/34
    • F41G7/301
    • The present invention relates to a method and an arrangement for guiding a missile. In accordance with the prior art, the angle position of a target (9) when the missile (3) is expected to reach the target is predicted on the basis of the angular velocity determined in a preceding time period. In order to improve the strike accuracy, the operator, in a second subsequent time period, tracks the actual position of the missile in relation to the predicted angle position of the target. If a deviation is observed, a correction command is transmitted to the missile in order to correct the missile trajectory. For this purpose, a communications link is provided to transmit the correction command given by the operator.
    • 本发明涉及一种用于引导导弹的方法和装置。 根据现有技术,基于在前一时间段中确定的角速度来预测当导弹(3)预期到达目标时目标(9)的角度位置。 为了提高打击精度,操作者在随后的第二时间段内追踪导弹的实际位置相对于目标的预测角度位置。 如果观察到偏差,则向导弹发送校正命令,以便校正导弹轨迹。 为此,提供通信链路以发送由操作者给出的校正命令。
    • 8. 发明公开
    • 위치 예측기법을 이용한 추적 장비간 비행 위치 정보 연동장치 및 방법
    • 使用位置预测技术在跟踪装置之间互锁飞行位置信息的方法和设备
    • KR20180022475A
    • 2018-03-06
    • KR20160107946
    • 2016-08-24
    • 국방과학연구소
    • KANG DO KEUNCHOI WON KYUNOH SANG WOOKPARK SO RYUNG
    • F41G7/22F41G7/30F41G9/00G01S13/66G01S13/88
    • F41G7/22F41G7/301F41G9/00G01S13/66G01S13/883
    • 본발명은 DDS((Data Distribution System) 기반의위치예측기법을이용한추적장비간비행위치정보연동장치및 방법에관한것으로, 동일한하나의비행체를추적하는복수의추적장비; 복수의추적장비에서수집되어입력된비행체의위치정보에추적장비간 우선순위를차등적용하여비행체의현재위치정보를추정하는위치정보모듈; 상기위치정보모듈에서추정된비행체의현재위치정보를기준으로특정미래시점에서의비행체의미래위치정보를예측하는위치예측모듈; 및상기예측된비행체의미래위치정보를자료연동토픽으로가공한후 자료처리장치를통해추적실패한추적장비로전송하는연동자료생성모듈;을포함한다.
    • 基于所述位置预测方法的本发明的DDS((数据分发系统)涉及一种飞行位置信息联锁装置和方法到磁道设备具有多个跟踪设备,用于跟踪所述飞行器中的同一个的;由所述多个跟踪装置的收集 差通过估计车辆位置信息模块的当前位置信息提供给跟踪装置所输入的车辆的位置信息之间的优先级;将来车辆eseoui某些相对于由位置信息模块估计出的车辆的当前位置信息的未来时间点 以及互锁数据生成模块,用于将预测的飞行对象的未来位置信息处理成数据链接主题并将数据传输到未能跟踪通过数据处理设备的跟踪设备。