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    FOLDING WING FOR A MISSILE AND A MISSILE HAVING AT LEAST ONE FOLDING WING ARRANGED THEREON
    1.
    发明授权
    FOLDING WING FOR A MISSILE AND A MISSILE HAVING AT LEAST ONE FOLDING WING ARRANGED THEREON 有权

    公开(公告)号：EP3165870B1

    公开(公告)日：2018-07-11

    申请号：EP16197396.1

    申请日：2016-11-04

    申请人： MBDA Deutschland GmbH

    发明人： Lutzenberger, Jörg

    IPC分类号： F42B10/14 ,  F42B10/16

    CPC分类号： F42B10/14 ,  F42B10/16

    摘要： A folding wing (2) for a missile comprises a wing root (6), an upper wing part (4) foldably supported at the wing root (6) around a swiveling axis (10), at least one first elastically pre-stressed force element and a latching device. The at least one first elastically pre-stressed force element (42) is coupled with the wing root (6) and the upper wing part (4) and is designed for permanently urging the upper wing part (4) into a working position relative to the wing root (6) through introducing a torque. The latching device is designed for arresting the upper wing part (4) on reaching the working position automatically.

    SYSTEM AND METHOD FOR GUIDING A CANNON SHELL IN FLIGHT
    3.
    发明公开
    SYSTEM AND METHOD FOR GUIDING A CANNON SHELL IN FLIGHT 审中-公开
    用于在飞行中引导CANNON壳体的系统和方法

    公开(公告)号：EP3246657A1

    公开(公告)日：2017-11-22

    申请号：EP17180536.9

    申请日：2011-08-24

    申请人： BAE Systems Rokar International Ltd.

    发明人： Malul, Assaf ,  Moshkovitz, Ziv

    IPC分类号： F42B10/64 ,  F42B10/14

    CPC分类号： F42B10/14 ,  F42B10/64

    摘要： An apparatus (14) and method for guiding a cannon shell accurately are disclosed. The apparatus includes two main parts (21) adapted to be installed on the leading end of the cannon shell. The front main part of the apparatus is equipped with at least one pair of fins and is rotatable with respect to the rear main part. The pair of fins is controlled to hold the front main part substantially stable with respect to an external reference frame when the cannon shell rotates as it flies towards its target. Control system is comprised within the apparatus that receives location signals and is adapted to provide guiding control commands to the cannon shell via the fins so as to guide the shell accurately to its preprogrammed target. The control system is adapted to activate the detonation chain of the shell according to preprogrammed mode.

    摘要翻译： 公开了一种用于精确地引导炮弹外壳的设备（14）和方法。 该设备包括两个主要部分（21），其适于安装在炮筒的前端上。 该装置的前部主要部分装备有至少一对翅片并且可相对于后部主部分旋转。 当炮弹向其目标飞行时，控制一对翅片以相对于外部参考框架将前主部件保持为基本稳定。 控制系统被包括在接收位置信号的设备内，并且适合于经由翅片向炮弹外壳提供引导控制命令，以便将外壳精确地引导到其预编程目标。 控制系统适用于根据预编程模式激活壳体的引爆链。

    FOLDING WING FOR A MISSILE AND A MISSILE HAVING AT LEAST ONE FOLDING WING ARRANGED THEREON
    4.
    发明公开
    FOLDING WING FOR A MISSILE AND A MISSILE HAVING AT LEAST ONE FOLDING WING ARRANGED THEREON 审中-公开
    折叠机翼就某型导弹和导弹，至少应该安排折叠机翼就

    公开(公告)号：EP3165869A1

    公开(公告)日：2017-05-10

    申请号：EP16197388.8

    申请日：2016-11-04

    申请人： MBDA Deutschland GmbH

    发明人： Lutzenberger, Jörg

    IPC分类号： F42B10/14 ,  F42B10/16

    CPC分类号： F42B10/16 ,  F42B10/14

    摘要： A folding wing (2) for a missile comprises a wing root (4), an upper wing part (6) foldable relative to the wing root (4), at least one guiding device (22, 24), and an elastically pre-stressed force element (48). The foldable upper wing part (6) comprises an end edge and a profile foot (10), wherein the wing root (4) comprises a base (26) and a receiving groove (12) opposite thereto, which receiving groove (12) is designed corresponding to the profile foot (10) at least in a ground (13) of the groove for receiving the profile foot (10) in a flush manner and is delimited by two delimiting edges (14, 16), which comprise a distance to each other, which at least equals the maximum profile thickness (36) of the profile foot (10). The at least one guiding device (22, 24) is arranged at one of the upper wing part (6) and the wing root (4) and is designed for guiding the profile foot (10) in a variable distance to the ground (13) of the receiving groove (12). The elastically pre-stressed force element (48, 50, 54, 56) is coupled with the wing root (4) and the upper wing part (6) and urges the upper wing part (6) into the receiving groove (12) through the pre-stress.

    摘要翻译： 的折叠翼（2），用于导弹上上翼部分包括翼根（4）（6）相对于机翼根部可折叠（4），至少一个引导装置（22，24），并在可弹性预 强调力元件（48）。 该可折叠上翼部（6）包括在端部边缘和轮廓脚（10），worin翼根（4）包括一底座（26）和一容纳槽（12）与其相对，其中接收槽（12）是 设计对应于至少轮廓脚（10）在槽的接地（13），用于以齐平的方式接收该轮廓脚（10）和由两个界定边缘（14，16），其包含的距离分隔 海誓山盟，其中至少等于轮廓脚（10）的最大轮廓厚度（36）。 所述至少一个引导装置（22，24）在所述上翼部（6）和翼根中的一个布置（4），并且被设计用于在可变距离引导轮廓脚（10）到地（13 ）所述接收槽（12）的。 弹性预应力力元件（48，50，54，56）耦合于机翼根部（4）和上翼部（6），并敦促上翼部（6）插入所述容纳槽（12）通过 预应力。

    FIN DEPLOYMENT MECHANISM FOR A PROJECTILE AND METHOD FOR FIN DEPLOYMENT
    6.
    发明公开
    FIN DEPLOYMENT MECHANISM FOR A PROJECTILE AND METHOD FOR FIN DEPLOYMENT 审中-公开
    肋骨使用的机制用于地板和方法使用RIB

    公开(公告)号：EP3055641A1

    公开(公告)日：2016-08-17

    申请号：EP14852587.6

    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.

    Nutating split petal flare for projectile fluid dynamic control
    10.
    发明公开
    Nutating split petal flare for projectile fluid dynamic control 审中-公开
    Mehrteiliges Nutationsauffaltelementfürfluiddynamische Projektilsteuerung

    公开(公告)号：EP2557388A1

    公开(公告)日：2013-02-13

    申请号：EP12179725.2

    申请日：2012-08-08

    申请人： The Boeing Company

    发明人： Bruns, Jon

    IPC分类号： F42B10/14 ,  F42B10/50

    CPC分类号： F42B10/14 ,  F42B10/50

    摘要： A system and methods for fluid dynamically controlling a projectile (100) are disclosed. At least one actuator (118) coupled to at least one common actuation structure (108) is actuated to provide an actuation force via the common actuation structure. The actuation force is transferred through at least one linkage structure to at least one fluid dynamic control surface (106) coupled thereto.

    摘要翻译： 公开了一种用于流体动态控制射弹（100）的系统和方法。 联接到至少一个公共致动结构（108）的至少一个致动器（118）被致动以通过公共致动结构提供致动力。 致动力通过至少一个连杆结构转移到与其耦合的至少一个流体动态控制表面（106）。