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    Control flap unit for projectiles or rockets
    2.
    发明授权
    Control flap unit for projectiles or rockets 失效
    用于射弹或火箭的控制挡板

    公开(公告)号：US3880383A

    公开(公告)日：1975-04-29

    申请号：US36651973

    申请日：1973-06-04

    Applicant: DYNAMIT NOBEL AG

    Inventor： VOSS ALFRED ,  KREUTZ HEINZ-WILHELM ,  KROSCHEL HEINZ ,  STRUNK MANFRED

    IPC: F42B10/14 ,  F42B13/32

    CPC classification number: F42B10/14

    Abstract: A control flap unit for a projectile of the type having a rudder carrier extending longitudinally and a plurality of guiding fins attached to the rudder carrier for pivotal movement about respective pivot axes extending perpendicular to the longitudinal axis of the projectile. A sliding sleeve is disposed internally of the rudder carrier for engagement with pivot levers mounted eccentrically with respect to the fin pivot axes so as to move the fins from a folded condition extending longitudinally along the outside of the rudder carrier to an in-flight position extending radially with respect to the rudder carrier. Lateral guide slots are provided in the rudder carrier for guiding the mounting end portions of the fins. Also, curved pivot lever guide slots are provided in the rudder carrier wall for guiding the pivot levers to effect the pivotal movement of the fins in response to longitudinal movement of the pivot levers resulting from engagement with the movable sliding sleeve. These pivot lever guide slots are constructed with an extension forwardly of the lateral slots so as to accommodate attachment and detachment of the fins with fixedly attached pivot levers onto the rudder carrier by merely inserting the pivot levers through the most forward portions of the pivot lever guide slot and then moving the fin into position in the lateral slots where the fins are pivotally connected to the rudder carrier by way of further connecting means through aligned apertures in the fins and the rudder carrier.

    Abstract translation: 一种用于具有纵向延伸的舵架的类型的抛射体的控制翼片单元和附接到舵架的多个引导翼片，用于围绕垂直于射弹的纵向轴线延伸的相应枢转轴线枢转运动。 滑动套筒设置在舵架的内部，用于与相对于翼片枢转轴线偏心安装的枢轴杆接合，以便使翼片从沿着舵架的外部纵向延伸的折叠状态移动到飞行位置，该飞行位置延伸 径向相对于舵架。 侧向引导槽设置在舵架中，用于引导翅片的安装端部。 此外，弯曲的枢转杆引导槽设置在方向舵托架壁中，用于引导枢转杆，以响应于由与可动滑动套筒接合而产生的枢转杆的纵向移动来实现翅片的枢转运动。 这些枢转杆引导槽构造为具有在侧向槽前面的延伸部分，以便通过仅枢转枢转杆将枢转杠杆穿过枢转杆导向件的最前部来容纳具有固定附接的枢轴的翼片的附接和拆卸 然后将翅片移动到横向狭槽中的位置，其中翅片通过另外的连接装置通过翅片和舵架中的对准的孔枢转地连接到舵架。

    Projectile or rocket preferably with unfolded tail unit
    3.
    发明授权
    Projectile or rocket preferably with unfolded tail unit 失效
    抛射体或火箭优选具有展开的尾部单元

    公开(公告)号：US3921937A

    公开(公告)日：1975-11-25

    申请号：US36675573

    申请日：1973-06-04

    Applicant: DYNAMIT NOBEL AG

    Inventor： VOSS ALFRED ,  STRUNK MANFRED ,  KROSCHEL HEINZ ,  KREUTZ HEINZ WILHELM

    IPC: F42B10/20 ,  F42B13/32

    CPC classification number: F42B10/20

    Abstract: A projectile, preferably a rocket with an unfoldable tail or rudder fin unit with a plurality of guiding fins movable between a storage position extending tangentially along the projectile to a flight position extending radially of the projectile longitudinal axis. A sliding sleeve is arranged in the projectile for engagement with pivot levers on the guiding fins so as to maintain the guiding fins in the storage position until a predetermined instant in the launching of the projectile, at which time the sliding sleeve engages the pivot levers to unfold the fins and force them into their flight position. The sliding sleeve is maintained in a first arresting position for holding the pivot levers and guide fins in the storage position by means of a connecting disk abutting the rear end of the sleeve. This connecting disk is attached to the projectile in such a manner that ignition of propellant charge means disposed rearwardly of the disk cause a disconnection of the disk with respect to the projectile, with a consequent falling away of the disk after the projectile has left a gun barrel so that a rocket engine disposed forwardly of the disk can operate unimpeded by the disk. The disk is provided with a throttle opening for accommodating transfer of propellant charge gases to ignite the rocket cruising engine and to assist a compression spring in moving the sleeve rearwardly to unfold the guiding fins. Preferred embodiments utilize the disk arrangement for accommodating the propellant charge initial acceleration and the later operation of the cruising engine with or without the further inclusion of the sliding sleeve for controlling foldable guide fins. Other features include a cup spring arrangement for holding a warhead detonator in position between detachably connected parts of the projectile, as well as novel conduit means for transferring the propellant charge gases to an ignition element for the crusing engine.

    Abstract translation: 抛物体，优选地具有可展开的尾部或方向舵翼单元的火箭，其具有多个引导翼片，所述引导翼片可在沿着射弹切向延伸到沿射弹纵向轴线径向延伸的飞行位置的存储位置之间移动。 滑动套筒布置在射弹中，用于与引导翅片上的枢转杆接合，以便将引导翅片保持在储存位置，直到发射弹丸的预定时刻为止，此时滑动套管与枢轴杆接合， 展开翅片并迫使它们进入飞行位置。 滑动套筒保持在第一止动位置，用于通过邻接套筒后端的连接盘将枢轴杆和导向翼片保持在收纳位置。 该连接盘以这样的方式附接到射弹，使得设置在盘的后方的推进剂充电装置的点火引起盘相对于射弹的断开，随后在射弹离开枪之后随之脱落 使得设置在盘前面的火箭发动机可以不受盘的影响而运行。 该盘具有节气门开口，用于容纳推进剂充气气体的转移以点燃火箭巡航发动机，并且帮助压缩弹簧向后移动套筒以展开引导翅片。 优选实施例利用盘装置来容纳推进剂充电的初始加速度和随后的运行中的巡航发动机，无论是否还包括用于控制可折叠导向翼片的滑动套筒。 其他特征包括用于将弹头雷管保持在弹射体的可拆卸连接部分之间的位置的杯形弹簧装置，以及用于将推进剂充气气体传送到用于破碎发动机的点火元件的新型导管装置。

    Process for the production of explosive devices surrounded by a case
    4.
    发明授权
    Process for the production of explosive devices surrounded by a case 失效
    通过案例生产爆炸装置的过程

    公开(公告)号：US3924510A

    公开(公告)日：1975-12-09

    申请号：US38703973

    申请日：1973-08-09

    Applicant: DYNAMIT NOBEL AG

    Inventor： STRUNK MANFRED ,  KROSCHEL HEINZ ,  VOSS ALFRED

    IPC: F42B1/036 ,  C06B21/02

    CPC classification number: F42B1/036

    Abstract: A process for the production of explosive devices surrounded by a case wherein an explosive charge is placed in a matrix mold and a pressing tool is moved in one direction of the mold to apply a force to one of mutually opposite end portions of the explosive device formed by the pressing operation. Subsequently, the explosive device is placed in a case having an open end with the other mutually opposite end portion proximate to the open end. A pressing tool is then moved to apply a force to the other mutually opposite end portion of the explosive device such that in the two pressing operations, a pressing tool is effective on the mutually opposite end portions to provide the explosive device with a uniform density. The process also includes the press molding of a detonation inhibiting barrier within the case prior to placing the explosive within the case and subsequently sealing the open end of the case with a sealing member.

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