Aeronautics and astronautics – Missile stabilization or trajectory control – Stabilized by rotation
Patent
1979-03-08
1981-10-27
Tudor, Harold J.
Aeronautics and astronautics
Missile stabilization or trajectory control
Stabilized by rotation
102501, 102520, F42B 1324, F42B 1514
Patent
active
042968933
ABSTRACT:
A projectile for shooting from a gun barrel in response to the force of a propellant gas emanating from the aperture of a propellant container, comprising a projectile body having a plurality of spin-producing propellant gas flow passages associated therewith, said passages annularly surrounding, and having their respective axes extending obliquely to, the longitudinal axis of the projectile body, wherein each passage has an inlet portion converging to an adjoining constricted portion, and a diverging portion extending downstream from the constricted portion, the axis of each passage being curved over the entire length of its converging inlet portion and substantially rectilinear over its diverging portion, and the walls of the diverging portion of each passage having a substantially rectilinear form, as viewed in the direction of propellant gas flow.
REFERENCES:
patent: 2559955 (1951-07-01), Hartwell
patent: 3058423 (1962-10-01), Laager
patent: 3394905 (1968-07-01), Rapp
patent: 3398682 (1968-08-01), Abela
patent: 3419230 (1968-12-01), Mainhardt et al.
patent: 3724781 (1973-04-01), Makow
patent: 3970004 (1976-07-01), Suter
patent: 4063511 (1977-12-01), Bullard
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