US4003531A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Reverse flow reaction control system
Assignee: United States Department of the Army
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Filing: 1975-05-06
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Granted: 1977-01-18
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Expires: 1995-05-06
Abstract
Abstract A control system for providing directional control to a missile during bo phase operation. The kinetic energy of the propellant exhaust gases is utilized to pump a vacuum in an annulus located around the rocket nozzle. To provide a reaction force to guide the missile, a closure is removed from one of several reaction nozzles located around the periphery of the aft end of the rocket and in communication with the vacuum chamber and the atmosphere. A thrust is generated by the air flowing through the reaction nozzle, into the vacuum chamber responsive to opening predetermined reaction nozzles.
Inventors
- 👤 Robert H. Fink
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 18:16
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/66; F42B10/663; F02; F02K; F02K9/00; F02K9/80
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
159 words
A directional control system for maintaining a missile on a launch predetermined path comprising: a. a body having forward, intermediate, and aft sections, said intermediate section enclosing a propellant and said aft section enclosing a nozzle in communication with said propellant; b. an annulus chamber carried in said aft section around said nozzle means for creating a vacuum in said chamber comprising an opening at the aft most end thereof whereby the kinetic energy of the burning propellant exhaust gases pump a vacuum in said annulus chamber, said annulus chamber having openings at predetermined positions around the periphery thereof for communication of said chamber with the atmosphere; c. closure means in each said opening; and, d. activating means for moving said closure means to selectively open said openings, whereby responsive to opening of said annulus chamber at said predetermined positions air is directed into said vacuum chamber at said predetermined position to create a control force on said missile.
Claim 2
Dependent Claim
159 words
A directional control system for maintaining a missile on a launch predetermined path comprising: a. a body having forward, intermediate, and aft sections, said intermediate section enclosing a propellant and said aft section enclosing a nozzle in communication with said propellant; b. an annulus chamber carried in said aft section around said nozzle means for creating a vacuum in said chamber comprising an opening at the aft most end thereof whereby the kinetic energy of the burning propellant exhaust gases pump a vacuum in said annulus chamber, said annulus chamber having openings at predetermined positions around the periphery thereof for communication of said chamber with the atmosphere; c. closure means in each said opening; and, d. activating means for moving said closure means to selectively open said openings, whereby responsive to opening of said annulus chamber at said predetermined positions air is directed into said vacuum chamber at said predetermined position to create a control force on said missile.
References Cited (Backward Citations)
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Cited
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Cited
US2968921A
Cited
US3048973A
Cited
US3140583A
Cited
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Cited
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Cited
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Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-01-18 | 1980-07-19 | 1981-01-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-01-18 | 1984-07-19 | 1985-01-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-01-18 | 1988-07-19 | 1989-01-18 | $7700.00 | Window Closed / Lapsed |