| 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 | Vanne de sécurité de type barométrique et dispositif pyrotechnique la comportant | EP93400452.4 | 1993-02-22 | EP0559520B1 | 1997-05-14 | Aubret, Jean-Pierre; Barriere, Michel |
| 2 | Vanne de sécurité de type barométrique et dispositif pyrotechnique la comportant | EP93400452.4 | 1993-02-22 | EP0559520A1 | 1993-09-08 | Aubret, Jean-Pierre; Barriere, Michel |
La vanne de sécurité (1) comporte un corps de vanne (2) dans lequel sont ménagés une chambre cylindrique (3) prolongée parallèlement à l'axe d'un alésage (16) interceptant un canal (12) connectant un orifice d'entrée (14) et un canal transversal de sortie (15). Une capsule manométrique étanche (4) est logée dans la chambre cylindrique et un coulisseau (17) lui est attelé et coulisse dans l'alésage en fonction des déformations de la capsule. Un verrou (19) s'étendant dans le canal empêche normalement toute communication entre l'orifice d'entrée (14) et le canal de sortie tant que le coulisseau empêche tout recul sensible de ce verrou au travers de l'alésage. Pour certaines positions du coulisseau ce recul est possible. |
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| 3 | Underwater grenade | US12043659 | 2008-04-09 | US07874252B2 | 2011-01-25 | Gabriel Soto; Calvin Clayson; Michael Haddon; Jerry Shultz |
| An underwater grenade and a method for using an underwater grenade. A depth activated, hand emplaced ordnance utilizing safe and arm technology to address underwater threats (such as enemy swimmers) while providing a safe interface with personnel. The grenade is armed after a sequence of events have occurred including reaching a desired depth and a desired passage of time. Failure of any of the events to occur will cause the grenade to be rendered safe. | ||||||
| 4 | Optical switch | US680317 | 1976-04-26 | US4023498A | 1977-05-17 | Paul Harris |
| An optical switch, which may be a part of a fuze for an explosive project, comprises a housing made up of a hollow cylindrical part with two end plates welded thereto and having a pair of aligned glass windows sealed through opposite sides for transmitting light transversely therethrough, a gas piston with O-ring seals slidable in the housing to define an end wall of a variable volume gas chamber therein and adapted to be moved by inertia during projectile launch to decrease the volume of the chamber and thereby increase the gas pressure, means for locking the piston in the new position, a valve in the housing for admitting a light attenuating gas to the chamber, an adjustable pressure relief valve in the housing adapted to open when the internal gas pressure exceeds the external pressure by a given amount, a light source positioned adjacent to the outside of one of the windows to project light through the windows and the attenuating gas, and a light-sensitive device positioned on the other side of the housing to receive the attenuated light. When the intensity of the light received by the device equals a critical value, the device responds by performing a desired function, such as arming a firing circuit of the fuze. The gas pressures in the chamber before and after piston movement are higher than a critical pressure at which the light reaching the output device has the critical value. When the projectile is projected to a desired altitude, the reduced atmospheric pressure causes the relief valve to open, reducing the chamber pressure below the critical pressure, thereby exciting the light sensitive device to arm the fuze.The switch may be used with a gas chamber of fixed volume, with a higher initial gas pressure. | ||||||
| 5 | Controlled actuator | US535014 | 1974-12-20 | US3984984A | 1976-10-12 | Francois X. Chevrier; Phillip L. Cogswell |
| An explosive initiator for a parachute rip cord release includes a hammer and firing spring mounted at one end of a cartridge chamber and an aneroid device and trigger mechanism mounted at its other end. A slidable sear extends along the cartridge chamber, connected at one end to the hammer and having a cam connection with the trigger mechanism at its other end. The normally uncocked hammer is manually cocked to slide the sear and thereby move the trigger mechanism into an operative position under control of the aneroid device. As ambient pressure decreases below a predetermined value, the aneroid device releases the trigger mechanism to thereby release its restraint upon motion of the sear and allow the spring to drive the hammer and detonate a cartridge in the chamber. Cartridge detonation drives an actuator piston that is connected to the parachute rip cord release. | ||||||
| 6 | Settable pneumatic altitude detection equipment | US39752673 | 1973-09-17 | US3827361A | 1974-08-06 | BARBIERI J; CHANG N; ZECHNOWITZ A; XENAKIS J |
| A settable pneumatic altitude detection device provides an electrical signal to a missile or projectile for arming and destructing the missile or projectile at preset altitudes. The present invention''s main structural elements are a pair of sphere supports which hold therein a rotatable sphere assembly. The sphere support structure has two spherically shaped gas bearing pads which are separated and fixedly held to a circularly shaped collar. Two separate gas supplies are operatively positioned in the sphere support structure and in the rotatable sphere. An electrical initiating signal causes a gas release mechanism and a time delay valve, for each gas supply, to controllably release gas therefrom. Gas is forced through peripherally positioned jet nozzles on the sphere, and through operatively positioned venting ports and calibrated orifices in the sphere support structure. After the missile is fired, the sphere is pneumatically uncaged from its polar supporting structure so that it can freely spin on a nearly frictionless gas cushion. A pneumatically controlled distance meter operatively located in the sphere activates pressure operated switches on the ascent and the descent of the missile trajectory. The aforesaid switches provide an electrical signal which arms the missile on ascent and causes the missile to self-destruct on descent.
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| 7 | Pressure actuated safety and arming device | US3675579D | 1970-02-25 | US3675579A | 1972-07-11 | MIN SHERMAN L |
| A safety and arming device having a spring biased bellows inflatable under air pressure of a predetermined magnitude. A tube is connected to the bellows and a stud is fixed to the inside of the tube. A shaft having a helical slot formed therein fits into the tube with the stud extending into the helical slot and an arming rotor is fixed to the end of the shaft. Under air pressure of a predetermined magnitude, the bellows expands and moves the tube which causes the stud, which is fixed to the inside of the tube and riding in the helical slot, to rotate the shaft and thereby rotate the arming rotor. A gear rack connected to the outside of the tube is in engagement with an escapement mechanism to limit the rate of travel of the bellows to preclude premature arming under the influence of shocks.
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| 8 | Ejector sensor fuze | US3631803D | 1968-04-24 | US3631803A | 1972-01-04 | DAVIS EDWARD J |
| A pneumatically operated fuze utilizing the force of the missile ejection position to break the hermetic seal and unlock the arming mechanism. The hermetic seal is a membrane covering the housing in which the fuze is mounted. The locking means are brackets which are straightened by the downward movement of the ejection piston. A bellows is then exposed to the dynamic pressure and expands causing the arming mechanism to arm.
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| 9 | Self-compensating barometric fuze | US3620165D | 1969-09-10 | US3620165A | 1971-11-16 | HENDERSON JOHN E |
| THE INVENTION RELATES TO BAROMETRIC FUZES FOR HIGH ALTITUDE ROCKETS AND PARTICULARLY TO A MECHANICAL SELF-COMPENSATING BAROMETRIC SENSING BELLOWS HAVING PRIOR TO LAUNCH, A FIXED END AND A FREE END, THE FREE END DESIGNED TO COMPENSATE FOR CHANGES IN ATMOSPHERIC PRESSURE. LANUCH ACCELERATION RELEASES A FIRING PIN WHICH FIRES A CHARGE DRIVING A PLUG INTO A MOVABLE SHAFT ATTACHED TO THE FREE END OF THE BELLOWS SENSIGN ELEMENT. THE PLUG FREEZES THE MOVEMENT OF THE SHAFT AND ESTABLISHES A REFERENCE BELLOWS LENGTH PROPORTIONAL TO THE AMBIENT ATMOSPHERIC PRESSURE IMMEDIATELY UPON LAUNCH. THE FIXED END IS THEN RELEASED TO SENSE ALTITUDE CHANGE. A TIME DELAY SAFETY SUBSEQUENTLY COACTS WITH THE BAROMETIC SENSING BELLOWS TO PREVENT FIRING AS THE ROCKET PASSES UPWARDLY THROUGH THE PRESELECTED FIRING ALTITUDES. THE SAFETY THEN RELEASES AN ALTITUDE SENSOR AT THE BELLOWS TO TRIGGER FUZE IGNITION ON THE DESCENT AT THE PRESELECTED ALTITUDE.
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| 10 | Pressure actuated fuze | US26462163 | 1963-03-12 | US3151557A | 1964-10-06 | EVANOFF PETER D; WROTEN JR JOHN F |
| 11 | Bomb fuze | US26920652 | 1952-01-31 | US2778311A | 1957-01-22 | ROBERTS GEORGE I; BEVINS JAMES E |
| 12 | Device to resist the disarming of bombs | US29158852 | 1952-06-03 | US2647465A | 1953-08-04 | JACOB RABINOW |
| 13 | Detonating mechanism | US47936643 | 1943-03-16 | US2422548A | 1947-06-17 | CHARLES HEBARD HUGH |
| 14 | Rocket ejection delay apparatus and/or method | US11488201 | 2006-07-17 | US20100237197A1 | 2010-09-23 | Gary C. Rosenfield; Robert A. Rosenfield |
| An ejection delay system, apparatus and/or method including an electronic ejection delay system having an ignition device; a power source connected to the ignition device; and, a flight parameter sensor switch electrically connected to the power source to initiate the provision of power from the power source to the ignition device; the electronic ejection delay system being disposed in some implementations in a housing system including a housing; a forward closure for closing the top end of the housing; and, an aft closure for closing the aft end of the housing. Also disclosed is a method for ejecting a rocket recovery system in flight; including sensing a parameter associated with flight; and, initiating deployment of a recovery system. | ||||||
| 15 | Controlled actuator | US491733 | 1974-07-25 | US3992999A | 1976-11-23 | Francois X. Chevrier; Leon Jones |
| A compact aneroid actuated explosive initiator for releasing a parachute upon descent to a predetermined altitude includes a firing pin releasably restrained by a rotatable sear that is urged toward release position. Cocking is achieved by compressing a driving spring without moving the firing pin, but concomitantly releasing a first restraint upon release of the sear. A second restraint upon release of the sear is provided by trigger levers under control of an aneroid barometer whereby the sear can be released and the firing pin driven by the firing spring only after cocking has been accomplished and a selected barometric condition exists. | ||||||
| 16 | Arming switch | US3601057D | 1969-02-11 | US3601057A | 1971-08-24 | KLINE RALPH S |
| An arming switch for making an electrical circuit through connections thereto upon a sudden reduction in ambient pneumatic pressure. A pair of parallel connected contact blades spring loaded toward a stationary contact are held separated therefrom by a skirted piston in a cylinder. The cylinder behind the piston normally fill to ambient pressure around the skirt. Whenever there is a sudden reduction in ambient pressure, the pressure differential across the piston moves the piston away from the blades and permits the blades to close against the stationary contact. Inherent leakage around the piston prevents gradual ambient pressure changes from producing arming action.
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| 17 | Environmental fuze device for air-dropped flares and the like | US3421442D | 1967-09-11 | US3421442A | 1969-01-14 | CLAIR DONALD R ST |
| 18 | Arming circuit with pressure responsive discharge switch | US7416960 | 1960-12-06 | US3198118A | 1965-08-03 | LORENZ JEROME L |
| 19 | Pressure responsive instrument | US1938260 | 1960-04-01 | US3129589A | 1964-04-21 | DAVID TATUM; MALTENFORT MARTIN S |
| 20 | Alititude switch | US23999351 | 1951-08-02 | US2748217A | 1956-05-29 | MELCHIOR FREDERICK C |
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