US3578796A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Spinning and stabilizing system for solid propellant rocket or missiles
Assignee: ATK Launch Systems LLC
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Filing: 1968-09-25
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Granted: 1971-05-18
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Expires: 1988-09-25
Abstract
Abstract A system for imparting a spin force to a solid propellant rocket while it is in a launch tube, and to stabilize the solid propellant rocket to discontinue the spin force after it leaves the launch tube.
Inventors
- 👤 Travis J Hagler
- 👤 William R Puckett
- 👤 Bobby G Tanner
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 19:26
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/62; F42B10/64; F42B10/02; F42B10/14; F42B10/16; F42B10/26; F42B10/28; F42B10/30
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
121 words
In a rocket or missile including a rocket motor case wherein a flow of gases is produced, and a nozzle secured to the aft end thereof and through which said gases flow, the improvement comprising the provision of a plurality of shafts mouNted thereon in parallel relationship to the longitudinal axis of said nozzle with a vane and a fin fixedly mounted on each shaft and the vanes positioned to have the impulse created by the flow of gases through the nozzle to impinge thereon to apply a spin force to the rocket or missile during the launch mode thereof and while the fins are not extended, and the vanes removed from the flow of gases when the fins are extended.
Claim 2
Dependent Claim
121 words
In a rocket or missile including a rocket motor case wherein a flow of gases is produced, and a nozzle secured to the aft end thereof and through which said gases flow, the improvement comprising the provision of a plurality of shafts mouNted thereon in parallel relationship to the longitudinal axis of said nozzle with a vane and a fin fixedly mounted on each shaft and the vanes positioned to have the impulse created by the flow of gases through the nozzle to impinge thereon to apply a spin force to the rocket or missile during the launch mode thereof and while the fins are not extended, and the vanes removed from the flow of gases when the fins are extended.
Claim 3
Dependent Claim
36 words
In a rocket or missile as in claim 1, the further improvement comprising the provision of a closure plate that is mounted in the nozzle and with vane retaining means attached only to the closure plate.
Claim 4
Dependent Claim
49 words
In a solid propellant rocket or missile as in claim 1, the further improvement comprising a notch engaging the edge of each of said fins to retain said fins in extended position to apply the stabilizing action to said solid propellant rocket or missile during the flight mode thereof.
References Cited (Backward Citations)
US2440271A
Cited
US2644296A
Cited
GB903842A
Cited
US3260205A
Cited
US3289587A
Cited
US3390850A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-05-17 | 1974-11-16 | 1975-05-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-05-17 | 1978-11-16 | 1979-05-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-05-17 | 1982-11-16 | 1983-05-18 | $7700.00 | Window Closed / Lapsed |