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1. 发明申请

WO2021240506A1 AIR VEHICLE AND METHOD FOR OPERATING THE AIR VEHICLE 审中-公开
公开(公告)号：WO2021240506A1
公开(公告)日：2021-12-02
申请号：PCT/IL2021/050597
申请日：2021-05-23
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： HOFI, Nissim , RYNSKI, Shuki
IPC分类号： B64C27/08 , B64C29/00 , B64C27/82 , G05D1/08
摘要： An air vehicle is provided including a body, a primary propulsion unit mounted to the body, and a set of secondary propulsion units mounted to the body. The primary propulsion unit includes at least one primary rotor and is configured for providing at least a majority of a total vertical thrust required for enabling vectored thrust flight to the air vehicle. The set includes at least three said secondary propulsion units. The set is configured for providing variable vectored thrust at least sufficient for generating control moments for stability and control of the air vehicle. The set of secondary propulsion units includes at least one secondary propulsion unit pivotably mounted with respect to the body about a respective pivot axis and configured for pivoting about the pivot axis between at least a vertical mode and a horizontal mode, to respectively provide a thrust vector at least in a range between a vertical thrust vector and a horizontal thrust vector. The pivotable secondary propulsion units are further configured for providing at least horizontal propulsion to the air vehicle at least when not in vertical mode.

2. 发明申请

WO2018127922A1 SAFETY DEVICE 审中-公开
公开(公告)号：WO2018127922A1
公开(公告)日：2018-07-12
申请号：PCT/IL2018/050020
申请日：2018-01-07
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： AMINOV, Gavriel , ZEHAVI, Eyal
IPC分类号： F42C15/34
摘要： Examples of safety devices for use with a munition are provided, the munition including a munition explosive and a safe and arm (S&A) device for activation of the munition explosive. In some examples the safety device includes a switch member and an actuation mechanism. The switch member is configured for being disposed between the munition explosive and the S&A device, the switch member being movable between at least two switch positions. In a first switch position (an arming prevention position (APP)), arming communication between the munition explosive and the S&A device is prevented. In a second switch position (an arming enabling position (AEP)), arming communication between the munition explosive and the S&A device is allowed. The actuation mechanism is configured for selectively moving the switch member at least from the APP to the AEP to thereby enable the S&A device, when armed, to detonate the munition explosive via the switch member.

3. 发明申请

WO2017199236A1 SYSTEMS AND METHODS FOR INDICATING AND RECOVERING PARACHUTE FAILURES 审中-公开
标题翻译：用于指示和恢复跳伞失败的系统和方法
公开(公告)号：WO2017199236A1
公开(公告)日：2017-11-23
申请号：PCT/IL2017/050529
申请日：2017-05-14
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： DEKEL, Guy , ZIVAN, Lior
IPC分类号： B64D17/00 , G01D1/00 , G05D1/00 , G06F19/00
CPC分类号： B64D17/00 , B64D17/22 , B64D17/62 , G01S13/08 , G01S13/88 , G01S13/89 , G01S17/08 , G01S17/88 , G01S17/89
摘要： A safety system for a parachute comprises at least a sensor configured to sense data indicative of the geometrical configuration of a canopy of the parachute, and at least a controller configured to extract data indicative of the geometrical configuration of the canopy from the sensed data, compare at least part of the extracted data with at least a reference configuration representing a normal operation of the parachute, detect a malfunction of the parachute based at least on said comparison, and, if a malfunction has been detected, command at least an actuator of the parachute or of the safety system, for performing a safety action. A safety system for a parachute is configured to trigger a safety action if a malfunction has been detected based on an analysis of data indicative of the geometrical configuration of suspension lines attached to a canopy of the parachute, or based on an analysis of the load of suspension lines.
摘要翻译：用于降落伞的安全系统包括至少一个传感器和至少一个控制器，所述传感器被配置为感测指示降落伞顶篷的几何构造的数据，所述控制器被配置为提取指示所述降落伞的几何构型来自感测数据的顶盖，将所提取的数据的至少一部分与表示降落伞的正常操作的至少一个参考配置进行比较，至少基于所述比较来检测降落伞的故障，并且如果已经检测到故障，至少命令降落伞或安全系统的致动器，以执行安全行动。用于降落伞的安全系统被配置为如果基于对指示附接到降落伞的伞面的悬挂线的几何构造的数据的分析或者基于对负载的分析而检测到故障来触发安全行动悬挂线。

4. 发明申请

WO2016170525A1 PROJECTILE, AND WARHEAD ASSEMBLY AND DEPLOYMENT SYSTEM THEREFOR 审中-公开
标题翻译：项目和战争组装及其部署制度
公开(公告)号：WO2016170525A1
公开(公告)日：2016-10-27
申请号：PCT/IL2016/050373
申请日：2016-04-07
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： OSDON, Tal , MARGOLIS , Herman , TIRASPOLSKI, Ilan
IPC分类号： F42B5/184
CPC分类号： F42B12/18 , F42B5/045 , F42B5/184 , F42B15/01
摘要： A warhead assembly is provided for a projectile includes a forward module having a precursor warhead, and an aft module including a main warhead. The warhead assembly includes a deployment system for selectively deploying the warhead assembly from a retracted configuration to a deployed configuration, at predetermined conditions, to thereby provide a longitudinal displacement between the forward module and the aft module. The deployment system includes an expansion member accommodated between the forward module and the aft module, and configured for being longitudinally expanded under the predetermined conditions to thereby increase a longitudinal dimension of the expansion member and thereby urge the forward module and the aft module away from one another to provide said longitudinal displacement. A corresponding deployment system and projectile are also provided.
摘要翻译：提供了一种用于射弹的弹头组件，其包括具有前体弹头的前进组件和包括主弹头的后部模块。弹头组件包括用于在预定条件下将弹头组件从缩回配置选择性地展开到展开配置的展开系统，从而在前模块和后模块之间提供纵向位移。展开系统包括容纳在前部模块和后部模块之间的膨胀构件，并且构造成在预定条件下纵向膨胀，从而增加膨胀构件的纵向尺寸，从而将前部模块和后部模块推离一个另一个提供纵向位移。还提供了相应的部署系统和弹道。

5. 发明申请

WO2016016889A1 PROPULSION SYSTEM 审中-公开
标题翻译：推进系统
公开(公告)号：WO2016016889A1
公开(公告)日：2016-02-04
申请号：PCT/IL2015/050775
申请日：2015-07-28
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： REGEV, Eyal
IPC分类号： B64C27/00 , B64C27/02 , B64C29/00 , F02B73/00
CPC分类号： B64C29/0033 , B64C27/28 , B64C39/024 , B64C2201/042 , B64C2201/104 , B64C2201/108 , B64D27/24 , B64D35/02 , B64D35/08 , B64D2027/026 , F02B61/04 , F02B73/00 , Y02T50/64
摘要： A propulsion system is provided, including a first propulsion unit, a second propulsion unit, a rotor, a first coupling and a second coupling. The first propulsion unit is configured for being fixedly mounted to an airframe. The rotor is configured for being pivotably mounted with respect to the first propulsion unit to allow selectively pivoting of the rotor from a horizontal mode to a vertical mode. The first coupling is configured for selectively coupling and decoupling the rotor with respect to the first propulsion unit. The second coupling is configured for selectively coupling and decoupling the rotor with respect to the second propulsion unit, independently of the first coupling.
摘要翻译：提供了一种推进系统，包括第一推进单元，第二推进单元，转子，第一联接器和第二联接器。第一推进单元构造成固定地安装到机身上。转子构造成相对于第一推进单元可枢转地安装，以允许转子从水平模式选择性地枢转到垂直模式。第一联接器构造成用于相对于第一推进单元选择性地联接和分离转子。第二联接器被配置为独立于第一联接件选择性地将转子相对于第二推进单元联接和解耦。

6. 发明申请

WO2015128861A1 FIN DEPLOYMENT SYSTEM 审中-公开
标题翻译： FIN部署系统
公开(公告)号：WO2015128861A1
公开(公告)日：2015-09-03
申请号：PCT/IL2015/050205
申请日：2015-02-24
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： OSDON, Tal
IPC分类号： F42B10/16 , F42B10/14
CPC分类号： F42B10/16
摘要： A fin deployment system for a projectile is provided, the fin deployment system defining a longitudinal axis and including: an actuator plate, a first mechanical stop arrangement, an actuation assembly, a plurality of fin assemblies, and a second mechanical stop arrangement. The actuator plate is pivotable from a first pivot position to a second pivot position about the longitudinal axis. The first mechanical stop arrangement is configured for initially locking the actuator plate at the first pivot position, and for selectively unlocking the actuator plate from the first pivot position responsive to an actuating force, to thereby allow the actuator plate to pivot to the second pivot position. The actuation assembly is for selectively applying the actuating force to the first mechanical stop arrangement, to thereby unlock the actuator plate from the first pivot position. Each fin assembly includes a fin pivotable from a stowed position to a deployed position about a respective fin hinge defining a respective deployment axis, each fin assembly forming a kinematic pair with the actuator plate such that the pivoting of the actuator plate between the first pivot position and the second pivot position, and the pivoting of each fin from the respective the stowed position to the respective the deployed position, are concurrent. The second mechanical stop arrangement is for locking the fin assemblies in the respective deployed positions responsive to the actuator plate pivoting from the first pivot position to the second pivot position.
摘要翻译：提供了一种用于射弹的翅片展开系统，翅片展开系统限定纵向轴线，并包括：致动器板，第一机械止动装置，致动组件，多个翅片组件和第二机械止动装置。致动器板可以从第一枢转位置枢转到关于纵向轴线的第二枢转位置。第一机械止动装置构造成用于将致动器板初始地锁定在第一枢转位置处，并且用于响应于致动力选择性地将致动器板从第一枢转位置解锁，从而允许致动器板枢转到第二枢转位置。致动组件用于选择性地将致动力施加到第一机械止动装置，从而将致动器板从第一枢转位置解锁。每个翅片组件包括翅片，其可以从收起位置枢转到关于限定相应展开轴线的相应翅片铰链的展开位置，每个翅片组件与致动器板形成运动学对，使得致动器板在第一枢转位置并且第二枢转位置以及每个翅片从相应的收起位置枢转到相应的展开位置是并行的。第二机械止动装置用于将散热片组件锁定在相应的展开位置，以响应致动器板从第一枢转位置枢转到第二枢转位置。

7. 发明申请

WO2014199371A8 AEROFOIL AND WINGS FOR AIR VEHICLES 审中-公开
公开(公告)号：WO2014199371A8
公开(公告)日：2014-12-18
申请号：PCT/IL2014/050513
申请日：2014-06-08
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： SHEPSHELOVICH, Michael , ABRAMOV, Danny
IPC分类号： B64C3/14 , B64C9/32
摘要： Two element aerofoils are provided, having an aerofoil chord, a primary element having a first leading edge and a first trailing edge, a secondary element having a second leading edge and a second trailing edge, a gap between the primary element and the secondary element, and an axial overlap between the first trailing edge and the second leading edge. The secondary element is deflectable with respect to the primary element about a fixed hinge point by a flap deflection angle. The secondary element is configured to operate in airbrake mode when deflected by a respective the flap deflection angle corresponding to a design airbrake deflection angle wherein to generate an airbrake drag. In at least some examples, the axial overlap is numerically greater than -0.5% of the aerofoil chord, at least for the design airbrake deflection angle. Also disclosed are methods for operating air vehicles, and methods for designing two-element aerofoils.

8. 发明申请

WO2011092688A1 DENTAL IMPLANTS, DEVICES AND METHODS ASSOCIATED WITH DENTAL IMPLANTATION PROCEDURES 审中-公开
标题翻译：牙科植入物，与牙科植入手术相关的装置和方法
公开(公告)号：WO2011092688A1
公开(公告)日：2011-08-04
申请号：PCT/IL2011/000083
申请日：2011-01-25
申请人： SIALO-LITE LTD. , HENIG, Itzhak , NAHLIELI, Oded , SHMUELI, Shmuel , JACOBSEN, Hagay
发明人： HENIG, Itzhak , NAHLIELI, Oded , SHMUELI, Shmuel , JACOBSEN, Hagay
IPC分类号： A61C8/00
CPC分类号： A61C8/0022 , A61C1/0046 , A61C1/0061 , A61C1/07 , A61C1/088 , A61C1/12 , A61C8/005 , A61C8/006 , A61C8/0068 , A61C8/0075 , A61C8/0089 , A61C8/0092 , A61C9/0046 , A61C17/02 , A61C17/04
摘要： A dental implant is provided. In some embodiments, the dental implant facilitates viewing an outside of a distal end thereof via a proximal opening thereof, and/or facilitates providing bone graft material via selectively closable one or more distal openings. A dental implant installation procedure is also provided in which a distal end of a dental implant is projected into a paranasal sinus cavity or a nasal cavity to thereby displace the respective sinus membrane or nasal cavity membrane from the respective cavity floor, while minimizing risk of damaging the respective membrane. Bone graft material is introduced into the space thereby created between the respective membrane and the respective cavity floor via a distal portion of the dental implant to thereby form a desired sinus augmentation.
摘要翻译：提供牙科植入物。在一些实施例中，牙科植入物有助于通过其近侧开口观察其远端的外侧，和/或有助于经由可选择地关闭的一个或多个远端开口提供骨移植材料。还提供牙科植入物安装程序，其中牙科植入物的远端突出到鼻旁窦腔或鼻腔中，从而将相应的窦膜或鼻腔膜从相应的腔底移位，同时使损伤的风险最小化各自的膜。骨移植材料通过牙科植入物的远侧部分引入空间，从而在相应的膜和相应的空腔底板之间形成，由此形成所需的窦扩大。

9. 发明申请

WO2022024112A1 REFUELING DEVICE 审中-公开
公开(公告)号：WO2022024112A1
公开(公告)日：2022-02-03
申请号：PCT/IL2021/050897
申请日：2021-07-25
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： SKLADMAN, Rami , DARMON, Ilan
IPC分类号： B64D39/00 , B64C9/32 , B64C9/36 , B64D3/02
摘要： Refueling devices for use in in-flight refueling operation are provided, including a body configured for being towed by a tanker aircraft and having a boom member that has a fuel delivery nozzle, a spatial control system and a longitudinal control system. The longitudinal displacement control system includes at least one panel element defining a front panel projected area orthogonal to a body longitudinal axis, each panel element being controllably and reversibly deployable incrementally to each one of a plurality of successive deployed positions between a fully retracted position and a fully deployed position, to provide a respective reversible incrementally increasing aft force to the refueling device at least during the in-flight refueling operation.

10. 发明申请

WO2021186436A1 FUEL TANK 审中-公开
公开(公告)号：WO2021186436A1
公开(公告)日：2021-09-23
申请号：PCT/IL2021/050287
申请日：2021-03-16
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： LEIBOVICH, Herman , YECHIEL, Liron , BLAUT, Rachel , LUSTER, Enbal , KATZ, Ofir , RUBIN, Eilon
IPC分类号： B60K15/03 , B32B5/08 , B32B5/28
摘要： The present disclosure provides a fuel-impermeable structural unit for use as a structural element of a fuel tank, including a multi-plies structure made of one or more composite material and polymers, and, a sealing polymeric film structurally bonded to and coating the entire surface of at least one face of the multi-plied structure. The polymeric film is integrated with an underlying external layer of said multi-plies structure, is impermeable to the fuel, is not reactive with the fuel, and can bind to an adhesive for fixing one or more rigid elements thereto.

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