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公开(公告)号：US3728936A
公开(公告)日：1973-04-24
申请号：US3728936D
申请日：1964-12-03
申请人： US NAVY
发明人： NORRIS B
CPC分类号： F42C15/30
摘要： 1. In a self-propelled fuel burning type missile of a character containing a nuclear warhead and adapted to be launched from a high speed aircraft, an arming and safing device for the warhead comprising, MEANS RESPONSIVE TO GAS PRESSURE FORCES GENERATED BY FUEL BURNED DURING MISSILE PROPULSION AND APPLIED IN A MANNER FOR DRIVING TIMER MECHANISMS AND CLOSING RESPECTIVE CONTACTS THEREON WHICH ARE INCORPORATED IN THE WARHEAD ARMING CIRCUIT, FIRST AND SECOND RELEASABLE LOCKING MEANS FOR SAID TIMER MECHANISMS DRIVING MEANS, ELECTRICALLY ACTUATED MEANS RESPONSIVE TO AN INTENT-TO-LAUNCH SIGNAL GENERATED FROM WITHIN THE LAUNCHING AIRCRAFT FOR UNLOCKING SAID FIRST LOCKING MEANS, AND MEANS RESPONSIVE TO FORCES AND/OR INFLUENCES OCCASIONED BY THE SEPARATION OF THE MISSILE FROM THE LAUNCHING AIRCRAFT FOR UNLOCKING SAID SECOND LOCKING MEANS.
摘要翻译： 1.在一枚含有核弹头的自燃燃料型导弹，适用于从高速飞机发射的一枚武器装备的武装装备，包括：燃油燃烧产生的燃气压力的反应 用于驱动定时器机构的主机并关闭在WARHEAD ARME电路中并入的第一和第二可释放锁定装置的定时器机构和闭合的锁定装置，用于定时器机构的驱动手段，电动启动装置响应于发起信号 从发射飞机起飞解除锁定的第一个锁定手段，并且意味着由分离飞机起飞解除锁定的第二个锁定手段的强制和/或影响的反应。
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公开(公告)号：US3853081A
公开(公告)日：1974-12-10
申请号：US77023558
申请日：1958-10-28
申请人： US NAVY
发明人： NORRIS B , WOOLSTON L , DAUDELIN R , FLUM R
摘要： A submarine torpedo tube launched missile type weapon having a water-to-air-to-water flight path, comprising, a covered rocket motor wherein the rocket motor cover is explosively released by explosive bolt devices subsequent to launching and during an initial portion of water travel flight. The rocket propelled weapon incorporates electrically controlled vanes for water guidance by influence over the exhaust discharge of the rocket motor together with separation means for severance of the rocket motor portion from the missile during air travel and guidance system controlled aerodynamic control surfaces for guidance to a predetermined water re-entry point.
摘要翻译： 潜艇鱼雷管发射具有水对空对水飞行路径的导弹型武器，包括覆盖的火箭发动机，其中火箭发动机盖在发射之后和在初始部分的水中爆炸性地释放 旅行飞行 火箭推进武器通过影响火箭发动机排气排放的电动控制叶片，并附有分离装置，用于在空中行驶期间将火箭发动机部分与导弹分开，并将导向系统控制的空气动力学控制表面引导到预定的 水再入点。
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