Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1989-07-21
1992-01-07
Carone, Michael J.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
23926519, 244 323, 60230, F42B 1030
Patent
active
050783360
ABSTRACT:
A simplified and cost-effective missile is disclosed which features a generally cylindrical casing, an aerodynamic warhead, and a plug nozzle. The casing of the missile contains a combustible propellant. The plug nozzle comprises a generally radially symmetric plug fitting within an open rear end of the casing such that an annular passageway is formed therebetween, through which exhaust gases from combustion of the propellant pass. The shape of the plug is chosen such that the cross-sectional area of the annular passageway varies in a predetermined fashion, to cause a desired thrust to be generated by combustion of the propellant. A number of vanes are spaced radially around the annular passageway and are inclined with respect to the centerline of the missile, so that the reaction of the exhaust gases on them provides a twisting force on the missile, whereby it spins and is stabilized in flight. In one embodiment, the vanes are not moved during the flight of the missile; in another embodiment, a servo-mechanism is provided for moving the vanes during the flight of the missile and thus altering its trajectory of flight.
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G. P. Sutton, Rocket Propulsion Elements, 5th ed., chart-p. 60 (pub. by Wiley-Interscience).
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