US3937144A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Internal stabilizing device for air and water missiles
Assignee: United States Department of the Navy
•
Filing: 1972-07-03
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Granted: 1976-02-10
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Expires: 1992-07-03
Abstract
Abstract An apparatus and method for reducing the launch disturbance of a weapon se on a supersonic aircraft is disclosed. The apparatus comprises a flywheel rotatably mounted within the store. The flywheel is pre-spun before launch using internal rockets or ram air. The spining flywheel produces a gyroscopic effect which appreciably reduces launch disturbance and therefore increases accuracy.
Inventors
- 👤 Peter Daniels
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 08:18
CPC Classifications
F; F42; F42B; F42B25/00
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
99 words
A nonself-propelling finless bomb adapted to be carried on and launched from aircraft at supersonic speeds comprising: a casing having suspension means thereon for mounting the bomb on the aircraft; an explosive warhead disposed within said casing; a flywheel fixed to a shaft mounted for rotation within said casing on the longitudinal axis thereof; and means for imparting rotation to said flywheel prior to launch whereby the angular momentum of the bomb is substantially increased, and its maximum angle of attack due to an angular rate correspondingly reduced, to minimize launch disturbances when the bomb separates from the aircraft.
Claim 2
Dependent Claim
99 words
A nonself-propelling finless bomb adapted to be carried on and launched from aircraft at supersonic speeds comprising: a casing having suspension means thereon for mounting the bomb on the aircraft; an explosive warhead disposed within said casing; a flywheel fixed to a shaft mounted for rotation within said casing on the longitudinal axis thereof; and means for imparting rotation to said flywheel prior to launch whereby the angular momentum of the bomb is substantially increased, and its maximum angle of attack due to an angular rate correspondingly reduced, to minimize launch disturbances when the bomb separates from the aircraft.
References Cited (Backward Citations)
US1316033A
Cited
US1316363A
Cited
US2402718A
Cited
US2406293A
Cited
US2691495A
Cited
US2729106A
Cited
US2849955A
Cited
US2960876A
Cited
US3610096A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1979-02-09 | 1979-08-11 | 1980-02-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-02-09 | 1983-08-11 | 1984-02-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-02-09 | 1987-08-11 | 1988-02-10 | $7700.00 | Window Closed / Lapsed |