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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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公开(公告)号：US3783310A
公开(公告)日：1974-01-01
申请号：US3783310D
申请日：1972-06-23
申请人： US NAVY
发明人： SEWELL C , VILLARROEL F , CAMPAGNUOLO C , MCKINDRA C , WOOLSTON L
CPC分类号： F42C15/29 , F41A19/60 , H02K7/1892 , H02K35/06
摘要： A system for firing aircraft rockets including a fluidic generator exposed to the airstream passing the launching aircraft in flight for generating the electrical power necessary to operate the firing circuit. The fluidic generator, produces a voltage output when a predetermined minimum air speed is achieved to charge capacitors in the firing circuit. Silicon controlled rectifiers are shunted across the capacitors to immediately discharge them when the aircraft decelerates below the predetermined minimum air speed.
摘要翻译： 一种用于发射飞机火箭的系统，包括暴露于通过飞行中的发射飞机的气流的流体发生器，用于产生操作击发电路所需的电力。 当实现预定的最小空气速度以对点火回路中的电容器充电时，流体发电机产生电压输出。 可控硅整流器在电容器之间分流，以便当飞机减速至预定的最低空气速度以下时立即将其排出。
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公开(公告)号：US3712170A
公开(公告)日：1973-01-23
申请号：US3712170D
申请日：1970-06-09
申请人： US NAVY
发明人： CAMPAGNUOLO C , MCKINDRA C , WOOLSTON L , SEWELL C , VILLARROEL F
CPC分类号： F42C15/29 , F41A19/60 , H02K7/1892 , H02K35/06
摘要： A system for firing aircraft rockets including a fluidic generator exposed to the airstream passing the launching aircraft in flight for generating the electrical power necessary to operate the firing circuit. The fluidic generator produces a voltage output when a predetermined minimum air speed is achieved to charge capacitors in the firing circuit. Silicon controlled rectifiers are shunted across the capacitors to immediately discharge them when the aircraft decelerates below the predetermined minimum air speed.
摘要翻译： 一种用于发射飞机火箭的系统，包括暴露于通过飞行中的发射飞机的气流的流体发生器，用于产生操作击发电路所需的电力。 当达到预定的最小空气速度以对点火回路中的电容器充电时，流体发生器产生电压输出。 可控硅整流器在电容器之间分流，以便当飞机减速至预定的最低空气速度以下时立即将其排出。
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