Subassembly means

Details Subassembly means Subassembly means

1994-12-16

1995-11-07

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Externally mounted stabilizing appendage

244 328, F42B 1014

Patent

active

054641730

ABSTRACT:
Improved collapsible roll or spin-stabilizing fin subassembly means of reively lightweight molded construction for missile means and the like that is generally made up of base or hub means, a series of four interconnecting fork means and a series of four fin means. The base means is suitably affixed in concentric fashion to the trailing end of the missile means. Each one of the interconnecting means is hingedly connected to its associated radially aligned bifurcated means of the series of four bifurcated means. At the same time, each fork means is biasingly interconnected to its associated bifurcated means so that any fork means is biasingly urged in a trailing or rearward direction, once the missile means is launched, to an outward and inward extended partially rotated position as limited by stop means provided on the base means. Each fin means has a curvature in one direction for facilitating collapsing of each fin means in matching surface-to-surface interengagement between opposed portions of the missile means and the storage/launch container therefor. Also, each one of the fin means is hingedly and biasingly interconnected to the outer end of its associated fork means; such that when the missile means is launched, each fin means is provided with stop means for limiting its rotational movement. By reason of the rearward partially rotated movement of each fork means about one axis together with the limited rotational movement of each fin means about another axis, each fin means is extended from its collapsed position to a preselected rearward extended swept-back rotational position when the missile means as provided on suitable platform means is launched from its container thereon, all for enabling enhanced roll or spin-stabilized rotation of the launched missile means about its axis throughout its trajectory or flight path.

REFERENCES:
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patent: 3333790 (1967-08-01), Durand, Jr.
patent: 3643599 (1972-02-01), Hubich
patent: 3880383 (1975-04-01), Voss et al.
patent: 3978790 (1976-09-01), Sandelius
patent: 4175720 (1979-11-01), Craig
patent: 4560121 (1985-12-01), Terp
patent: 5211357 (1993-05-01), Leidenberger

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