US3777666A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Safety device for a gyratory rocket missile
Assignee: Mefina SA
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Filing: 1971-10-28
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Granted: 1973-12-11
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Expires: 1991-10-28
Abstract
Abstract A safety device for a gyratory rocket missile of the type with a primer support centrifugally pivotable from a safe to an armed position and centrifugally releasable means for securing the support in the safe position, comprises an axially slidable pin urged by a spring to a position locking the securing means in support-securing positon. The two ends of a resilient open loop releasably engage a groove in the pin to hold it in the locking position and, when the pin moves due to an axial acceleration upon firing the missile so as to free the securing means, the ends of the loop come to bear against a shoudler of the pin to prevent return thereof. Once the support regulated by a delay mechanism reaches the armed position, a finger slidably mounted in an outwardly opening radial housing in the primer support moves out of its housing to lock the support in position.
Inventors
- 👤 R Morel
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 16:29
CPC Classifications
F; F42; F42C; F42C14/00; F42C15/00; F42C15/20; F42C15/22; F42C15/24; F42C15/26
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
276 words
In a safety device for a gyratory rocket missile, said device comprising a primer support member movable under the action of centrifugal force upon gyration of the missile between a safe position and an armed position, means for releasably securing the support in the safe position, said securing means being movable under the action of centrifugal force upon gyration of the missile from a support-securing position to a position in which the support is freed, the improvement comprising means for releasably locking the securing means in the support-securing position, said locking means comprising a retaining member slidably mounted parallel to the axis of the missile between a first position in which it locks the securing means in the support-securing position and a second position in which the securing means is freed, a spring opposing movement of the locking means from the first position to the second position upon axial acceleration of the missile, stop means for holding said retaining member in the second position, said stop means comprising an elastic element bearing transversely against the retaining member, said elastic element being removably engaged in a recess in the retaining member when the retaining member is in the first position, said elastic element comprising an open twoended loop of resilient wire, the two ends of said loop being disposed on opposite sides of the retaining member, said retaining member comprising a cylindrical pin having a peripheral groove forming said recess, and a rod of lesser diameter than said pin extending from an end of said pin and forming a shoulder therewith, said elastic element engaging against said shoulder when the retaining member is in the second position.
Claim 2
Dependent Claim
276 words
In a safety device for a gyratory rocket missile, said device comprising a primer support member movable under the action of centrifugal force upon gyration of the missile between a safe position and an armed position, means for releasably securing the support in the safe position, said securing means being movable under the action of centrifugal force upon gyration of the missile from a support-securing position to a position in which the support is freed, the improvement comprising means for releasably locking the securing means in the support-securing position, said locking means comprising a retaining member slidably mounted parallel to the axis of the missile between a first position in which it locks the securing means in the support-securing position and a second position in which the securing means is freed, a spring opposing movement of the locking means from the first position to the second position upon axial acceleration of the missile, stop means for holding said retaining member in the second position, said stop means comprising an elastic element bearing transversely against the retaining member, said elastic element being removably engaged in a recess in the retaining member when the retaining member is in the first position, said elastic element comprising an open twoended loop of resilient wire, the two ends of said loop being disposed on opposite sides of the retaining member, said retaining member comprising a cylindrical pin having a peripheral groove forming said recess, and a rod of lesser diameter than said pin extending from an end of said pin and forming a shoulder therewith, said elastic element engaging against said shoulder when the retaining member is in the second position.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-12-10 | 1977-06-11 | 1977-12-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-12-10 | 1981-06-11 | 1981-12-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-12-10 | 1985-06-11 | 1985-12-11 | $7700.00 | Window Closed / Lapsed |