Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1990-09-10
1991-10-08
Hellner, Mark
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
102202, 102381, F42B 1518
Patent
active
050547127
ABSTRACT:
A spin-stabilized projectile with a correctable trajectory, wherein the projectile possesses lateral or transverse thrust-propulsion devices which are distributed about the circumference thereof, each incorporating an impulse-generating charge inclusive an electrically-activatable detonator arranged beneath a cover which is radially ejectable relative to the longitudinal axis of the projectile. The detonator, with the presence of a connecting cable which initially extends coaxially with the cover and then thereafter extends at an angle relative thereto, is arranged in the transitional region intermediate the impulse-generating charge and the cover, whereby the cover, with conformance of its external contour to the contour of the encompassing casing surface of the projectile, is fixed to the structure of the projectile across a rupture location, which is hermetically sealed radially inwardly of the impulse-generating charge with respect to the center of the projectile.
REFERENCES:
patent: 3034434 (1962-05-01), Swaim et al.
patent: 4211378 (1980-07-01), Crepin
patent: 4503773 (1985-03-01), Bolieau
patent: 4982913 (1991-01-01), Miller
Bar Klaus
Lehrieder Gunther
Diehl GmbH & Co.
Hellner Mark
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