Aeronautics and astronautics – Missile stabilization or trajectory control – Stabilized by rotation
Patent
1993-01-04
1994-07-12
Tudor, Harold J.
Aeronautics and astronautics
Missile stabilization or trajectory control
Stabilized by rotation
102439, 102517, 244 33, F42B 1026
Patent
active
053281306
ABSTRACT:
A cylindrical device connected to the nose of a projectile for imparting n to the projectile fired from a non-rifled bore of a cannon. The device has at least two coaxial, adjacent, and integrally connected cylindrical segments of different diameter. The segment having the larger diameter is positioned most rearwardly of the projectile, relative to the nose of the projectile, and the periphery of this segment has circumferentially spaced angled slots for catching air moving past the projectile to spin the projectile. The segment with the smaller diameter attaches the cylindrical device to the aft end of the nose of the projectile and directs the flow of air to and through the angled slots of the segment having the larger diameter.
REFERENCES:
patent: 463922 (1891-11-01), Russell
patent: 2946261 (1960-07-01), Crockett
patent: 3487780 (1970-01-01), Troen et al.
patent: 4249465 (1981-02-01), Ballmann
patent: 4682546 (1987-07-01), Chouich
Farina Anthony
Gilman Stewart
Goldberg Edward
Lane Anthony T.
Sachs Michael C.
The United States of America as represented by the Secretary of
Tudor Harold J.
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