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31. 发明申请

WO98043038A1 METHOD AND DEVICE FOR A FIN-STABILISED BASE-BLEED SHELL 审中-公开
标题翻译：用于稳定稳定的基底壳的方法和装置
公开(公告)号：WO98043038A1
公开(公告)日：1998-10-01
申请号：PCT/SE1998/000438
申请日：1998-03-11
IPC分类号： F42B10/16 , F42B10/40 , F42B10/14
CPC分类号： F42B10/40 , F42B10/16
摘要： The present invention relates to a method and a device designed for use with such shells (1) that are equipped with a base-bleed unit (8) for extended range and which during the first phase of their trajectory are spin-stabilised but which in the subsequent phase are subjected to spin deceleration by fins (9-13) that deploy from the shell body and take over the stabilising function. More exactly the present invention is a method and a device that enables the said shells (1) to achieve an effective and functional deployment of the fins (9-13) at the desired point in time with simultaneous ejection of the base-bleed unit (8) which at this point in time either no longer performs any useful function since it is burnt-out and solely constitutes a dead-weight or its function is no longer required. The basic idea behind the present invention is that the base-bleed unit (8) and the fin protector (19) that initially surrounds the fins (9-13) shall be permanently integrated with each other and thereby can be removed/ejected as a single unit.
摘要翻译：本发明涉及一种设计用于与这种壳体（1）一起使用的方法和装置，所述壳体（1）装备有用于延伸范围的基底泄放单元（8），并且在其轨迹的第一阶段期间旋转稳定，随后的相位通过从壳体展开并接管稳定功能的翅片（9-13）进行旋转减速。更确切地说，本发明是一种方法和装置，其使得所述壳体（1）能够在期望的时间点上实现散热片（9-13）的有效和功能性部署，同时喷射基底排放单元（ 8）在现在这个时间点不再执行任何有用的功能，因为它被烧毁，只是构成一个重量，或者不再需要它的功能。本发明背后的基本思想是，最初围绕翅片（9-13）的基底排气单元（8）和翅片保护器（19）应该彼此永久地一体化，从而可以作为单一单位。

32. 发明申请

WO1995031689A1 MISSILE WITH DEPLOYABLE CONTROL FINS 审中-公开
标题翻译：有可配置的控制FINS
公开(公告)号：WO1995031689A1
公开(公告)日：1995-11-23
申请号：PCT/US1995005901
申请日：1995-05-11
申请人： HUGHES AIRCRAFT COMPANY
发明人： HUGHES AIRCRAFT COMPANY , SMITH, John, D. , LAMBERTON, Ryan, D.
IPC分类号： F42B10/14
CPC分类号： F42B10/14
摘要： A missile includes a missile body and a structure for controlling the flight path of the missile body. The control structure includes at least one control fin (28) and an actuator shaft (40) that supports the control fin (28) for rotational missile control movement about a control axis (30) prependicular to the axis of the missile body. A deployment shaft (42) extending from the control fin is rotatable in a deployment shaft bore (46) in the actuator shaft (40) and permits the control fin to rotate from a folded position parallel and adjacent to the missile body to an extended position parallel to the control axis.
摘要翻译：导弹包括导弹体和用于控制导弹体飞行路径的结构。控制结构包括至少一个控制翅片（28）和致动器轴（40），该致动器轴（40）支撑控制翅片（28），用于围绕垂直于导弹体轴线的控制轴线（30）进行旋转导弹控制运动。从控制翅片延伸的展开轴（42）可以在致动器轴（40）中的展开轴孔（46）中旋转，并允许控制翼从平行和邻近导弹体的折叠位置旋转到延伸位置平行于控制轴。

33. 发明申请

WO2022245267A1 PROJECTILE AND FUSE WITH FIN 审中-公开
公开(公告)号：WO2022245267A1
公开(公告)日：2022-11-24
申请号：PCT/SE2022/050447
申请日：2022-05-09
申请人： BAE SYSTEMS BOFORS AB
发明人： HAGBERG, Anders
IPC分类号： F42B10/14 , F41G7/00 , F42B10/00 , F42B10/50 , F42B10/64 , F42C19/02 , F42B14/00
摘要： The invention concerns a projectile (1) outfitted with a target finder, intended to be fired from a launching device, comprising one or several fins (3) where the fins (3, 3´), upon being extended, cause the projectile (1) to be urged into a controlled oscillating movement. The invention also concerns a fuse.

34. 发明申请

WO2022245265A1 PROJECTILE AND FUSE WITH BRAKE 审中-公开
公开(公告)号：WO2022245265A1
公开(公告)日：2022-11-24
申请号：PCT/SE2022/050430
申请日：2022-05-04
申请人： BAE SYSTEMS BOFORS AB
发明人： PETTERSSON, Thomas , JOHANSSON, Björn
IPC分类号： F42B10/50 , F42B7/00 , F42B10/00 , F42B10/14 , F42B10/16 , F42B10/64 , F42C19/02 , F42B14/00
摘要： The invention concerns a projectile (1) outfitted with a target finder (5), intended to be fired from a launching device, comprising one or several brake flaps (3, 3´) where the brake flaps (3, 3´), after their being extended, cause the projectile (1) to be arranged in a controlled oscillating movement. The invention also concerns a fuse.

35. 发明申请

WO2019028259A1 MID BODY SEEKER PAYLOAD 审中-公开
公开(公告)号：WO2019028259A1
公开(公告)日：2019-02-07
申请号：PCT/US2018/045021
申请日：2018-08-02
申请人： BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION INC.
发明人： CHOINIERE, Michael J. , BATCHELDER, Jason H. , EVANS, Peter J. , HALLERMAN, Gregory R.
IPC分类号： F42B10/14 , F42B10/62 , F41G7/20 , F41G7/22 , F41G7/26
摘要： A mid-body which a cylindrical housing which defines a longitudinal axis and has an interior compartment. A guidance controller is housed within the mid-body for controlling flight. A plurality of wings are connected to the housing and each of the wings is movable into a deployed position to provide guidance during flight. The mid-body has an access window which facilitates communication between the interior compartment of the housing and an external environment. A normally door covers the access window, but when the door is moved, relative to the access window, into an open position, communication between the interior compartment and the external environment is established. An optical sensor is accommodated within the interior compartment and the optical sensor, once the door is moved relative to the access window, can view the external environment and supply data to the guidance controller for controlling operation of the plurality of wings during flight.

36. 发明申请

WO2017037698A1 FOLDABLE WINGS FOR AN UNMANNED AIR VEHICLE 审中-公开
标题翻译：一个不可思议的空中车辆的折叠线
公开(公告)号：WO2017037698A1
公开(公告)日：2017-03-09
申请号：PCT/IL2016/050935
申请日：2016-08-25
申请人： UVISION AIR LTD
发明人： KAHLON, Moshe , MORAG, Amit
IPC分类号： F42B10/14 , B64C3/56
CPC分类号： B64C3/56 , B64C39/024 , B64C2201/102 , B64C2201/201 , B64C2201/203 , F42B10/14
摘要： An unmanned air vehicle (UAV) having a fuselage, a foldable propulsion means to generate thrust leading to the UAV movement, a driving means to drive the propulsion means and a plurality of flight control surfaces actuators are further included. The UAV further includes at least one pair of foldable wings where the rear portion of the wings is pivotally attached to the fuselage. The wings having at least one roll control surface hinged to at least one of the foldable wings. At least a pair of tail stabilizers having ruddervators flight control surfaces hinged to the tail stabilizers. In a fully extended position or in ready to fly state position, each of the foldable wings are deployed perpendicular to one another and perpendicular to the fuselage to form an offset-x shaped wings, and in a stowed position, each of the wings are positioned parallel to one another and positioned parallel to the fuselage.
摘要翻译：具有机身的无人驾驶飞行器（UAV），产生通向无人机移动的推力的可折叠推进装置，还包括驱动推进装置的驱动装置和多个飞行控制面致动器。无人机还包括至少一对可折叠的翼，其中翼的后部可枢转地附接到机身。所述翼具有铰接到所述可折叠翼中的至少一个的至少一个滚动控制表面。至少一对具有舵机飞行控制面的尾部稳定器铰接到尾部稳定器上。在完全延伸的位置或准备飞行状态的位置，每个可折叠翼彼此垂直并垂直于机身展开以形成偏移x形的翼，并且在收起位置中，每个翼定位彼此平行并且平行于机身定位。

37. 发明申请

WO2014203237A3 SHUTTER MECHANISM FOR COVERING A WING DEPLOYMENT OPENING 审中-公开
标题翻译：用于覆盖部署开放的快门机制
公开(公告)号：WO2014203237A3
公开(公告)日：2016-02-25
申请号：PCT/IL2014050422
申请日：2014-05-14
申请人： RAFAEL ADVANCED DEFENSE SYS
发明人： SAROKA ARIE , SCHOENMANN AMNON
IPC分类号： B64C1/14 , F42B10/14
CPC分类号： B64C1/14 , B64C3/40 , B64C7/00 , B64C9/02 , F42B10/14 , F42B10/38 , Y02T50/145 , Y02T50/32
摘要： A shutter mechanism for covering a wing's spreading opening formed in an airborne body and a method for covering such opening while implementing the shutter mechanism, wherein the shutter comprises at least one flap assembly, and wherein from the instant that a deployed wing of the airborne body passed and moved over it, it is biased by traction of at least one springy element to an angular motion around an axis, unto a condition where the flap component of the assembly is positioned so that it is substantially conformal to the outline of the outer surface of the fuselage of the airborne body and while it covers the opening through which the wing passed in its motion; and from an instant that the wing returned and connected to the flap component of the assembly, the flap is biased to an angular motion counter the spring, to the state that the wing returns and is relocated on its top surface.
摘要翻译：一种用于覆盖形成在空气传播体中的机翼传播开口的快门机构和一种在实现快门机构的同时覆盖这种开口的方法，其中快门包括至少一个挡板组件，并且其中从空中机体的部署翼通过并在其上移动，它被至少一个弹性元件的牵引力偏压到围绕轴线的角运动，其中组件的折翼部件被定位成使得其基本上与外表面的轮廓一致机身的机身，同时它覆盖机翼通过其运动的开口; 并且从翼返回并连接到组件的翼片部件的瞬间，翼片被偏压到与弹簧相反的角运动，到翼返回并被重新定位在其顶表面上的状态。

38. 发明申请

WO2015053679A1 FIN DEPLOYMENT MECHANISM FOR A PROJECTILE AND METHOD FOR FIN DEPLOYMENT 审中-公开
标题翻译： FIN部署的FIN部署机制和FIN部署方法
公开(公告)号：WO2015053679A1
公开(公告)日：2015-04-16
申请号：PCT/SE2014/000125
申请日：2014-10-07
申请人： BAE SYSTEMS BOFORS AB
发明人： CARLQVIST, Lars-Åke , ERIKSSON, Pär
IPC分类号： F42B10/14 , F42B10/54 , F42B10/64
CPC分类号： F42B10/14 , F42B10/50 , F42B10/54 , F42B10/64
摘要： The invention relates to a fin deployment mechanism (10, 20) for a rotationally stabilized projectile (1), comprising at least one fin (2, 15) and at least one actuator, in which the fin (2, 15) is arranged in a deployable and retractable manner on the projectile (1), and in that the fin (2, 15) and at least one balance weight (3, 17) are mechanically arranged so that, when the fin (2, 15) is deployed by the actuator, then the balance weight (3, 17) is displaced in towards the centre (6) of the projectile (1) and, when the fin (2, 15) is retracted by the actuator, then the balance weight (3, 17) is displaced out from the centre (6) of the projectile (1). The invention also relates to a method for energy-efficient deployment and retraction of fins (2, 15) on a rotating projectile, in which at least one fin (2, 15) is arranged in a deployable and retractable manner on the projectile, and in which the fin (2, 15) is fitted to at least one balance weight (3, 17) according to: (a) when the fin (2, 15) is displaced out from the centre of the projectile, upon deployment of the fin (2, 15), the balance weight (3, 17) is displaced in towards the centre of the projectile, (b) when the fin (2, 15) is displaced in towards the centre of the projectile, upon retraction of the fin, the balance weight (3, 17) is displaced out from the centre of the projectile.
摘要翻译：本发明涉及一种用于旋转稳定的射弹（1）的翅片展开机构（10,20），其包括至少一个翅片（2,15）和至少一个致动器，其中翅片（2,15）布置在在射弹（1）上可展开和可缩回的方式，并且翅片（2,15）和至少一个平衡重（3,17）机械地布置成使得当翅片（2,15）被执行器，然后平衡重（3,17）朝向射弹（1）的中心（6）移位，并且当翅片（2,15）被致动器缩回时，平衡重（3， 17）从射弹（1）的中心（6）移出。本发明还涉及一种用于在旋转射弹上的翅片（2,15）的节能展开和回缩的方法，其中至少一个翅片（2,15）以可展开和可缩回的方式布置在射弹上，以及其中所述翅片（2,15）根据以下方式装配到至少一个平衡重（3,17）：（a）当所述翅片（2,15）从所述射弹的中心偏离时，翅片（2,15），平衡重（3,17）朝着射弹的中心位移，（b）当翅片（2,15）朝着射弹的中心移位时，平衡重（3,17）从射弹的中心移出。

39. 发明申请

WO2011126970A2 COMPRESSION SPRING WING DEPLOYMENT INITIATOR 审中-公开
标题翻译：压缩弹簧部署发动机
公开(公告)号：WO2011126970A2
公开(公告)日：2011-10-13
申请号：PCT/US2011031074
申请日：2011-04-04
申请人： BAE SYS INF & ELECT SYS INTEG , PIETRZAK AMY , KRUEGER MICHAEL J
发明人： PIETRZAK AMY , KRUEGER MICHAEL J
IPC分类号： F42B10/14 , F42B10/16
CPC分类号： F42B10/18
摘要： A wing deploy initiator for deploying guidance wings of a rocket or missile, such as the APKWS, provides enhanced wing deploy performance with reduced complexity, cost, and likelihood of failure. The invention includes a cam which is driven between the stowed guidance wings by at least one compression spring, thereby forcing the guidance wings outward through slots in the fuselage of the rocket or missile. Oblique flat sides of the cam can push against beveled edges on the wings. The cam can be attached to spring mandrels, and the cam and mandrels can pass through a retaining plate as the springs decompress. Embodiments can exert sufficient push force to enable the wings to break through frangible slot covers. An embodiment applicable to the APKWS includes only 13 parts, and can exert up to 10 lb push force on each wing after 0.3 inches of wing travel.
摘要翻译：用于部署火箭或导弹的引导翼（例如APKWS）的机翼部署启动器以降低的复杂性，成本和故障可能性提供增强的机翼部署性能。本发明包括一个凸轮，该凸轮通过至少一个压缩弹簧在收起的引导翼之间被驱动，由此迫使引导翼向外穿过火箭或导弹的机身中的狭槽。凸轮的倾斜平面可以推动翼上的斜边。凸轮可以连接到弹簧心轴上，当弹簧减压时，凸轮和心轴可以穿过保持板。实施例可以施加足够的推力以使翼能够突破易碎的槽盖。适用于APKWS的实施例仅包括13个部件，并且可以在0.3英寸机翼行程之后在每个机翼上施加高达10lb的推力。

40. 发明申请

WO2011019424A2 GUIDED MISSILE 审中-公开
标题翻译：导弹
公开(公告)号：WO2011019424A2
公开(公告)日：2011-02-17
申请号：PCT/US2010/035178
申请日：2010-05-18
申请人： RAYTHEON COMPANY , UNGER, Michael P. , WITHERSPOON, Stephen D. , SCHLEINING, James T.
发明人： UNGER, Michael P. , WITHERSPOON, Stephen D. , SCHLEINING, James T.
IPC分类号： F42B10/14
CPC分类号： F42B10/14 , F42B10/64
摘要： A missile (10) comprising a projectile body (20), a payload (60) contained within the nose portion (30), wings (70) stowed within the mid portion (40), and fins (80) stored within the tail portion (50). The wings (70) can be deployed during intermediate stages of the flight path when lift is advantageous, and re-stowed during terminal stages when an almost vertical angle-of-attack is desired. The fins (80) function as stabilizing components during the early ballistic stage of the flight path and function as guiding components thereafter.
摘要翻译：一种包括抛射体（20），包含在鼻部（30）内的有效载荷（60），装载在中间部分（40）内的翼部（70）以及翅片（60）的导弹（10）（80）存储在所述尾部（50）内。当飞行路线的中间阶段时，翼部（70）可以在升力有利时展开，并且在期望几乎垂直的迎角时在末端阶段重新收起。翅片（80）在飞行路线的早期弹道阶段起到稳定部件的作用并且其后用作引导部件。

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