US3760589A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Throttling mechanism for controlling the thrust level of a solid propellant rocket motor
Assignee: ATK Launch Systems LLC
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Filing: 1969-03-24
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Granted: 1973-09-25
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Expires: 1989-03-24
Abstract
Abstract A throttling mechanism for the nozzle of a solid propellant rocket motor that is capable of selectively controlling the effective area of the discharge orifices of the nozzle whereby the magnitude of the thrust of the solid propellant rocket motor may be varied.
Inventors
- 👤 R Overall
- 👤 Haye J De
- 👤 W Puckett
- 👤 J Kelly
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 19:26
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/80; F02K9/86
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
114 words
In a throttling mechanism for use with a nozzle for a solid propellant rocket motor having at least one discharge orifice therein comprising, means positioned adjacent said discharge orifices and adapted to cover or uncover said discharge orifices to vary the magnitude of thrust of said solid propellant rocket motor, said means comprising at least one piston adapted to move over said discharge orifice to vary the size thereof, said throttling mechanism being mounted in the aft end of said propellant rocket motor, a molded insert of insulation mounted in the aft end adjacent said nozzle and means defining semi-circular grooves in said insert and said nozzle to provide cylinders for positioning said pistons.
Claim 2
Dependent Claim
114 words
In a throttling mechanism for use with a nozzle for a solid propellant rocket motor having at least one discharge orifice therein comprising, means positioned adjacent said discharge orifices and adapted to cover or uncover said discharge orifices to vary the magnitude of thrust of said solid propellant rocket motor, said means comprising at least one piston adapted to move over said discharge orifice to vary the size thereof, said throttling mechanism being mounted in the aft end of said propellant rocket motor, a molded insert of insulation mounted in the aft end adjacent said nozzle and means defining semi-circular grooves in said insert and said nozzle to provide cylinders for positioning said pistons.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-09-24 | 1977-03-26 | 1977-09-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-09-24 | 1981-03-26 | 1981-09-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-09-24 | 1985-03-26 | 1985-09-25 | $7700.00 | Window Closed / Lapsed |