子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | Dual device for the arming of a missile either by means of an electrical signal or by manual mechanical operation | EP80830089 | 1980-10-30 | EP0029014A3 | 1981-09-16 | Marrocco, Francesco; Notargiacomo, Enzo M. |
The invention is a dual device for effecting the arming of a missile either by means of an electrical signal which operates a motor or by means of a suitable key which is operated manually. The mechanical device is based principally on the use of a differential the two crown wheels of which are connected respectively to the motor and the mechanism operated by the key. The crown wheels via the pinions independently move the shaft which communicates the movement to the missile actuater. |
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| 2 | Dual device for the arming of a missile either by means of an electrical signal or by manual mechanical operation | EP80830089.1 | 1980-10-30 | EP0029014A2 | 1981-05-20 | Marrocco, Francesco; Notargiacomo, Enzo M. |
The invention is a dual device for effecting the arming of a missile either by means of an electrical signal which operates a motor or by means of a suitable key which is operated manually. The mechanical device is based principally on the use of a differential the two crown wheels of which are connected respectively to the motor and the mechanism operated by the key. The crown wheels via the pinions independently move the shaft which communicates the movement to the missile actuater. |
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| 3 | JPS5230800B2 - | JP8998872 | 1972-09-07 | JPS5230800B2 | 1977-08-10 | |
| 4 | JPS4844408A - | JP10151372 | 1972-10-09 | JPS4844408A | 1973-06-26 | |
| 5 | JPS5121280B1 - | JP8709071 | 1971-11-01 | JPS5121280B1 | 1976-07-01 | |
| 6 | JPS4837999A - | JP8998872 | 1972-09-07 | JPS4837999A | 1973-06-04 | |
| 7 | Shock hardened initiator and initiator assembly | US14625144 | 2015-02-18 | US09879951B2 | 2018-01-30 | Bradley Biggs; Timothy B. Bonbrake; George Darryl Budy; Christopher Schott |
| An initiator assembly includes an initiator housing having an initiator cavity and a housing orifice edge. A bridge substrate is positioned within the initiator cavity, the bridge substrate includes a substrate base including a uniform first planar surface and first and second bridge contacts flush with the uniform first planar surface. The first and second bridge contacts form a continuous planar mounting surface. An explosive charge and a flyer plate are within the initiator cavity, the flyer plate interposed between the explosive charge and the bridge substrate. A plunger head is telescopically received in the initiator cavity and includes an anchoring cylinder face having a face perimeter and extends between first and second face ends. The housing orifice edge is anchored to the anchoring cylinder face at a position between the first and second face ends and extends around the face perimeter. | ||||||
| 8 | SHOCK HARDENED INITIATOR AND INITIATOR ASSEMBLY | US14625144 | 2015-02-18 | US20160178333A1 | 2016-06-23 | Bradley Biggs; Timothy B. Bonbrake; George Darryl Budy; Christopher Schott |
| An initiator assembly includes an initiator housing having an initiator cavity and a housing orifice edge. A bridge substrate is positioned within the initiator cavity, the bridge substrate includes a substrate base including a uniform first planar surface and first and second bridge contacts flush with the uniform first planar surface. The first and second bridge contacts form a continuous planar mounting surface. An explosive charge and a flyer plate are within the initiator cavity, the flyer plate interposed between the explosive charge and the bridge substrate. A plunger head is telescopically received in the initiator cavity and includes an anchoring cylinder face having a face perimeter and extends between first and second face ends. The housing orifice edge is anchored to the anchoring cylinder face at a position between the first and second face ends and extends around the face perimeter. | ||||||
| 9 | Micro-delayed detonator for ballistic rockets and rockets thus equipped | US476206 | 1974-06-04 | US3982487A | 1976-09-28 | Adelin F. Richelle; Hans D. Harnau |
| The invention pertains to a micro-detonator having a first cap and a second cap associated to a delaying charge. Said caps are respectively located in housings separated by a diaphragm having a striking protrusion to fire the second cap. | ||||||
| 10 | Firing delay for point detonating fuze | US3786754D | 1968-12-20 | US3786754A | 1974-01-22 | CAMMACK T; SCHMIDT R; DONAHUE W; GRATTON P |
| A mechanical delay for point detonating fuzes for projectiles to allow penetration into aircraft or similar light target structures before detonation of the projectile. A trans-axial inertial firing pin is mounted within the projectile so that the centrifugal force exerted thereon by the spinning projectile during light target penetration will selectively determine the firing time delay. Alternatively, instantaneous detonation is provided by a second, axial firing pin when the projectile strikes an impenetrable target or one of such hardness that would break up the projectile before the trans-axial firing pin could react to provide the normal delayed detonation.
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| 11 | Control apparatus | US3636880D | 1968-12-13 | US3636880A | 1972-01-25 | ASKE ROBERT L |
| A velocity decay actuated self-destruct mechanism for use with stabilized projectiles. Dynamic pressure against a nose cap due to movement of the projectile through a fluid medium is balanced by spring pressure from within the ogive of the projectile. Movement of the nosepiece as the spring pressure overcomes the dynamic pressure causes self-destruct of the projectile.
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| 12 | Ammunition antidefuzing device | US3599570D | 1969-08-28 | US3599570A | 1971-08-17 | INGERSOLL WILLIAM C; SHEPHERD JACK W |
| A device consisting of a container, which is filled with a liquid chemical material having combustion characteristics, that is positioned in a bomb or shell in conjunction with the fuze therefor, so that upon impact of the bomb or shell with the target, the container will be ruptured and cause the liquid chemical material to be dispersed in the explosive in the bomb or shell and in the event the bomb or shell is a dud, that any attempts to remove the fuze therefrom, will result in the liquid chemical material being exposed to the atmosphere, water or the perspiration of any one removing the fuze, to cause the liquid chemical material to combust and thus ignite or detonate the explosives within the bomb or shell.
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| 13 | Clockwork time fuzes | US3530797D | 1966-12-21 | US3530797A | 1970-09-29 | KAISER PAUL; MUELLER JOSEF |
| 14 | Percussion fuse for rocketprojectiles | US18197037 | 1937-12-27 | US2145507A | 1939-01-31 | JOSEPH DENOIX PAUL EMILE |
| 15 | SHOCK HARDENED INITIATOR AND INITIATOR ASSEMBLY | US14257181 | 2014-04-21 | US20140224142A1 | 2014-08-14 | Bradley Biggs; Timothy B.` Bonbrake; George Darryl Budy; Christopher Schott |
| Embodiments of an initiator support assembly that includes an initiator housing including an initiator cavity system are generally described herein. In some embodiments, a bridge substrate is positioned within the initiator cavity. The bridge substrate includes a substrate base including a uniform first planar surface and an opposed second surface. The bridge substrate further includes a first bridge contact extending over the substrate base. The first bridge contact is substantially flush with the first planar surface. A second bridge contact extends over the substrate base. The second bridge contact is substantially flush with the first planar surface. The first and second bridge contacts and the uniform first planar surface form a continuous planar mounting surface. An explosive charge, positioned within the initiator cavity, includes a charge mounting surface that is continuously coupled in surface-to-surface contact across the continuous planar mounting surface. | ||||||
| 16 | Shock hardened initiator and initiator assembly | US13022164 | 2011-02-07 | US08701557B2 | 2014-04-22 | Bradley Biggs; Timothy B. Bonbrake; George Darryl Budy; Christopher Schott |
| Embodiments of an initiator support assembly that includes an initiator housing including an initiator cavity system are generally described herein. In some embodiments, a bridge substrate is positioned within the initiator cavity. The bridge substrate includes a substrate base including a uniform first planar surface and an opposed second surface. The bridge substrate further includes a first bridge contact extending over the substrate base. The first bridge contact is substantially flush with the first planar surface. A second bridge contact extends over the substrate base. The second bridge contact is substantially flush with the first planar surface. The first and second bridge contacts and the uniform first planar surface form a continuous planar mounting surface. An explosive charge, positioned within the initiator cavity, includes a charge mounting surface that is continuously coupled in surface-to-surface contact across the continuous planar mounting surface. | ||||||
| 17 | Mechanically operated fuse for gyratory missiles | US29229372 | 1972-09-26 | US3882782A | 1975-05-13 | SIMMEN ROBERT |
| A fuse provided with safety means operative before firing and during the beginning of the flight of the missile, said fuse including an escapement controlling a toothed sector which is adapted after a lapse of time defined by the escapement to shift a primer carrier into an intermediate position for which centrifugal force urges said carrier into its operative position corresponding to alignment of the actual primer between the striker and the detonator.
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| 18 | Safety and arming mechanism | US45899954 | 1954-09-28 | US3877378A | 1975-04-15 | CLARK FITZHUGH T; THEODORE DAVID T |
| 1. In a fuze for an explosive projectile having a base section, a body section, and a nose section, a safety and arming mechanism including a firing train having a booster charge and acceleration-sensitive means for initiating fuze arming when the projectile to which the fuze is affixed is fired from a gun, the improvement comprising: an impact assembly located in the nose portion of the fuze, said impact assembly comprising a cartridge containing a dust under pressure, means for releasing said dust from said cartridge after the projectile to which the fuze is affixed is airborne, the action of the dust passing over the projectile serving to deposit an electrostatic charge upon the projectile.
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| 19 | Fluidic thermoelectric generator | US26773972 | 1972-06-30 | US3839094A | 1974-10-01 | CAMPAGNUOLO C |
| A thermoelectric generator that utilizes the high temperature generated by fluid compression waves within a resonant tube that is subject to a supersonic air stream. The resonant tube, which may take any one of a number of forms, is located in a nose cone of the projectile that has a nozzle formed at the ogive for directing the fluid flow created while the projectile is in flight onto the open end of the resonant tube. This fluid flow sets up complex cyclical compression waves within the resonant tube which subsequently causes heating of the fluid therein due primarily to the friction within the tube and to the nonisentropic compression of the fluid interacting with the shock waves therein. The heating of the fluid and the high amplitude fluctuations cause a thermoelectric crystal placed near the closed end of the resonant tube to emit an electrical output. The electrical output may be utilized as a power source for any of a number of electrical devices within the projectile.
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| 20 | Fuse for the safe and precise detonation of explosive projectiles | US3734023D | 1971-12-09 | US3734023A | 1973-05-22 | KAISER P; WEBER R |
| A detonating fuse for a fired, spinning projectile, which fuse includes a primer-supporting rotor which is prevented from being moved from a safety to a firing position by means of a springbiased safety lever. The safety lever is prevented from swinging out, under the influence of centrifugal force, by means of a rotatable spring core member. The core member is locked against rotation by an anchor until the projectile is fired at which time the anchor is released and the core member is rotated in a predetermined angle by a draw spring to release the safety lever. Continued rotation of the core member releases a pair of swingable levers to enable a biasing means to push a firing pin into the rotor which has been moved to its firing position by centrifugal force. The core member and safety lever further include mutually engageable stops to prevent unintentional detonation during transport.
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