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。