US4291849A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Reaction-jet torquer
Assignee: United States Department of the Army
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Filing: 1979-05-04
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Granted: 1981-09-29
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Expires: 1999-05-04
Abstract
Abstract A reaction-jet torquer system carried in a projectile to aim the projectileo a target. The torquer system uses the thrust of sonic nozzles to control a gyro rotor inertial frame of reference. The reaction force applied to the gimbal gives the rotor the capability of tracking the target. A sensor carried by the gyro provides logic which identifies and activates the appropriate nozzle or nozzles of the system to generate the required gimbal force.
Inventors
- 👤 Aubrey Rodgers
- 👤 Escar L. Bailey
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 16:48
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/22; F41G7/2213; Y; Y10; Y10T; Y10T74/00; Y10T74/12; Y10T74/1229; Y10T74/1232; Y10T74/1239
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
171 words
In a missile disposed for flight to a target, apparatus for controlling flight of said missile to said target comprising: a. a gyro assembly including a frame secured to said missile, an outer gimbal secured to said frame, an inner gimbal secured to said outer gimbal, and, a rotor mounted in said inner gimbal; b. reaction-jet torquer means carried in said inner gimbal for torquing said rotor to line of sight with said target, said reaction jet torquer means including a source of pressurized gas carried in said inner gimbal, four sonic nozzles spaced about said inner gimbal 90° apart, four miniature electrically actuated solenoid valves disposed about said inner gimbal 90° apart, each said valve disposed in communication with said source of gas and one of said nozzles; c. a sensor carried by said inner gimbal for receiving signals from said target and for transmitting signals for activation of said reaction-jet torquer means, and; d. control means for guiding said missile to the target response to torquing of said rotor.
Claim 2
Dependent Claim
171 words
In a missile disposed for flight to a target, apparatus for controlling flight of said missile to said target comprising: a. a gyro assembly including a frame secured to said missile, an outer gimbal secured to said frame, an inner gimbal secured to said outer gimbal, and, a rotor mounted in said inner gimbal; b. reaction-jet torquer means carried in said inner gimbal for torquing said rotor to line of sight with said target, said reaction jet torquer means including a source of pressurized gas carried in said inner gimbal, four sonic nozzles spaced about said inner gimbal 90° apart, four miniature electrically actuated solenoid valves disposed about said inner gimbal 90° apart, each said valve disposed in communication with said source of gas and one of said nozzles; c. a sensor carried by said inner gimbal for receiving signals from said target and for transmitting signals for activation of said reaction-jet torquer means, and; d. control means for guiding said missile to the target response to torquing of said rotor.
Claim 3
Dependent Claim
28 words
Apparatus as in claim 1 wherein said sensor is divided into quadrants, each said quadrant being electrically connected to a respective said solenoid valve for selective activation thereof.
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) | 1984-09-28 | 1985-03-30 | 1985-09-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-09-28 | 1989-03-30 | 1989-09-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-09-28 | 1993-03-30 | 1993-09-29 | $7700.00 | Window Closed / Lapsed |