Patent US3726496A successfully refreshed from Google Patents.
US3726496A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Tridirectional actuator
Assignee: United States Department of the Army
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Filing: 1971-08-04
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Granted: 1973-04-10
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Expires: 1991-08-04
Abstract
Abstract The device is a portion of a missile control system used to generate the forces to change missile attitude. A three channel fluid amplifier with its exits located at 120* intervals around the missile body in a plane orthogonal to the long axis is the motive device. It is controlled by a single, electrically driven port venting mechanism, which is energized by an electronically generated sequence of pulses. These switching pulses are formed to produce a proper force time product in the pitch and yaw planes without cross coupling.
Inventors
- 👤 J Leonard
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 05:55
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/80; F02K9/805; F02K9/82; F42; F42B; F42B10/00; F42B10/60; F42B10/66; F42B10/663
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
132 words
A missile attitude control system comprising: a tridirectional fluid amplifier having an inlet and three outlets; means for supplying high pressure fluid to the inlet of said fluid amplifier; conduit means connecting said outlets from said fluid amplifier to three exhaust ports located 120* apart around the periphery of said missile adjacent the rear end thereof, the gas eminating from said exhaust ports in a plane orthogonal to the longitudinal axis of said missile; vent means in said fluid amplifier; valve means for selectively closing said vent means to direct the gas flow into selected outlets; and means for controlling said valve means comprising an electronic circuit for sequencing flow through the three exhaust ports into six time intervals in equal cycle times, three for controlling pitch and three for controlling yaw.
Claim 2
Dependent Claim
132 words
A missile attitude control system comprising: a tridirectional fluid amplifier having an inlet and three outlets; means for supplying high pressure fluid to the inlet of said fluid amplifier; conduit means connecting said outlets from said fluid amplifier to three exhaust ports located 120* apart around the periphery of said missile adjacent the rear end thereof, the gas eminating from said exhaust ports in a plane orthogonal to the longitudinal axis of said missile; vent means in said fluid amplifier; valve means for selectively closing said vent means to direct the gas flow into selected outlets; and means for controlling said valve means comprising an electronic circuit for sequencing flow through the three exhaust ports into six time intervals in equal cycle times, three for controlling pitch and three for controlling yaw.
Claim 3
Dependent Claim
37 words
A missile attitude control system as set forth in claim 1 wherein, said sequencing means includes means for varying the length of the on time interval for each of the six intervals within a constant cycle time.
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) | 1976-04-09 | 1976-10-09 | 1977-04-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-04-09 | 1980-10-09 | 1981-04-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-04-09 | 1984-10-09 | 1985-04-10 | $7700.00 | Window Closed / Lapsed |