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1. 发明授权

US4275680A Anchoring system 失效
标题翻译：锚定系统
公开(公告)号：US4275680A
公开(公告)日：1981-06-30
申请号：US71468
申请日：1979-08-31
申请人： John W. Pennington, III , Kenneth G. Thorsted
发明人： John W. Pennington, III , Kenneth G. Thorsted
IPC分类号： B63B21/28 , E02D5/80
CPC分类号： E02D5/80 , B63B21/28
摘要： An anchoring system comprising a pointed anchor body having either a wire apped therearound in one embodiment thereof or a coiled wire disposed within a hollow portion of the anchor body in a second embodiment thereof. One end of the wire is fixed to the pointed end of the anchor body and the other end projects through a pusher plate at the other end of the anchor body, behind which is an explosive or propellant charge for actuating the anchor. When the charge is ignited the anchor body is driven out of the charge housing, which is configured to retain the pusher plate, causing the wire to unwind as the anchor body embeds itself.
摘要翻译：一种锚固系统，其包括在其一个实施例中具有缠绕在其上的线的尖形锚体，或者在其第二实施例中设置在锚固体的中空部分内的螺旋线。电线的一端固定在锚固体的尖端上，另一端通过锚固体另一端的推板突出，在该主体后方是用于致动锚的炸药或推进剂装药。当电荷被点燃时，锚体被驱动离开充电壳体，其被构造成保持推动板，使得导线随着锚固体自身嵌入而放松。

2. 发明授权

US4497460A Erodale spin turbine for tube-launched missiles 失效
标题翻译：用于管发射导弹的Erodale自旋涡轮机
公开(公告)号：US4497460A
公开(公告)日：1985-02-05
申请号：US478747
申请日：1983-03-25
申请人： Kenneth G. Thorsted , John W. Pennington
发明人： Kenneth G. Thorsted , John W. Pennington
IPC分类号： F42B10/30 , F42B13/24
CPC分类号： F42B10/30
摘要： An erodable spin turbine having a plurality of turbine blades affixed to the outer periphery of a missile nozzle. When the missile is fired in its launch tube the exhaust gas stream flows across the turbine blades to impart an angular torque to the missile as it traverses the launch tube. As the missile traverses the launch tube the exhaust gas stream is also eroding the spin turbine such that when the missile exits the launch tube the missile has reached its terminal spin rate and the spin turbine is effectively eroded so that it no longer interacts with the exhaust gas stream. The spin rate of the missile in its free-flight trajectory is maintained by airflow over canted fins and canards mounted on the missile's airframe.
摘要翻译：一种可旋转的旋转涡轮机，其具有固定到导弹喷嘴外周的多个涡轮机叶片。当导弹在其发射管中被射击时，废气流在涡轮叶片上流动，以在导弹穿过发射管时赋予导弹角扭矩。当导弹穿过发射管时，废气流也侵蚀了自旋涡轮机，使得当导弹离开发射管时，导弹已经达到其终端旋转速率，并且旋转涡轮机被有效地侵蚀，使得其不再与排气物相互作用气流。导弹在其自由飞行轨迹中的旋转速度由安装在导弹的机身上的倾斜翅片和卫星上的气流保持。

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