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    • 1. 发明授权
    • Missile fin locking mechanism
    • 导弹鳍片锁定机构
    • US06250584B1
    • 2001-06-26
    • US09419544
    • 1999-10-18
    • William W. HsuDuncan D. Bragg
    • William W. HsuDuncan D. Bragg
    • F42B1006
    • F42B10/14
    • A locking mechanism for moveable control fins extending from the surface of a missile. The locking mechanism includes a pin extending thru the outer surface of the missile into an opening provided in the movable fin. A link is pivotally connected between each of the pins and a slide member disposed internally of the missile and carried by a guide. The links are in a close to dead center position when the pins are extended into the openings in each of the fins. Upon a command signal from a controller, preparatory to missile launch, a restraining device holding the slide is removed and a spring commences movement of the slide toward a position which will take the links past their dead center position upon which additional springs which are loaded around each of the pins are activated to positively move the slide and extract the pins from the openings in the fins.
    • 用于从导弹表面延伸的可移动控制翼的锁定机构。 锁定机构包括延伸穿过导弹的外表面的销,设置在可动翅片中的开口中。 一个连杆在每个销之间枢转地连接,一个滑动构件设置在导弹的内部并由导向件承载。 当销延伸到每个翅片的开口中时,连杆处于靠近死点的位置。 根据来自控制器的命令信号,准备发射导弹,去除了保持滑块的约束装置,并且弹簧开始使滑块朝着使链接超过它们的死点位置的位置移动,在该位置上,加载有附加弹簧 每个销被激活以主动地移动滑块并从翅片中的开口提取销。