US4023749A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Directional control system for artillery missiles
Assignee: United States Department of the Army
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Filing: 1975-12-08
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Granted: 1977-05-17
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Expires: 1995-12-08
Abstract
Abstract Apparatus for controlling the powered flight phase of an artillery rocket a straight line as determined by a 2° of freedom gyroscope with spin axis aligned along the missile axis. The flight path is made insensitive to crosswinds, launching transients, and missile thrust malalignments, without requiring lateral acceleration measurements.
Inventors
- 👤 William C. McCorkle, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 22:42
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/34; G; G05; G05D; G05D1/00; G05D1/08; G05D1/0808; G05D1/0816
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
105 words
A directional control system for maintaining a missile on a launch predetermined path comprising: a. a gyroscope mounted with its spin axis and rotor aligned with the longitudinal axis of said missile at launch; b. actuating means including a plurality of jet vanes disposed in pairs about the aft end of said missile; c. acceleration switch means for differentially canting said vanes for producing a spin to said missile responsive to initial acceleration thereof; d. control means for receiving signals from said gyro and actuating said actuator means for deflecting opposing pairs of jet vanes in unison in proportion to gyro pitch and yaw signals.
Claim 2
Dependent Claim
105 words
A directional control system for maintaining a missile on a launch predetermined path comprising: a. a gyroscope mounted with its spin axis and rotor aligned with the longitudinal axis of said missile at launch; b. actuating means including a plurality of jet vanes disposed in pairs about the aft end of said missile; c. acceleration switch means for differentially canting said vanes for producing a spin to said missile responsive to initial acceleration thereof; d. control means for receiving signals from said gyro and actuating said actuator means for deflecting opposing pairs of jet vanes in unison in proportion to gyro pitch and yaw signals.
Claim 3
Dependent Claim
26 words
A directional control system as set forth in claim 1 wherein said plurality of jet vanes is comprised of four vanes disposed in equally spaced relation.
Claim 4
Dependent Claim
37 words
A directional control system as in claim 2 wherein said actuator means includes four electrical actuators, each respectively connected to one of said jet vanes to receive said gyro signals for the deflection of said jet vanes.
Claim 5
Dependent Claim
21 words
A directional control system as set forth in claim 3 including chain drive means connecting said jet means and said actuators.
Claim 6
Dependent Claim
35 words
A directional control system as set forth in claim 4 wherein said control system further includes amplifier means for receiving pitch and yaw signals from said gyro and for transmitting said signals to said actuators.
References Cited (Backward Citations)
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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) | 1980-05-16 | 1980-11-15 | 1981-05-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-05-16 | 1984-11-15 | 1985-05-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-05-16 | 1988-11-15 | 1989-05-17 | $7700.00 | Window Closed / Lapsed |