Guided projectile flight control fin system

Details Guided projectile flight control fin system Guided projectile flight control fin system

1984-08-15

1986-01-21

Kyle, Deborah L.

Aeronautics and astronautics

Missile stabilization or trajectory control

Externally mounted stabilizing appendage

244 31, 244 323, 244 33, 416102, 416151, F42B 1330, F42B 1516, F42B 1514

Patent

active

045653402

ABSTRACT:
A guidance system for small spinning projectiles which is mechanically simple, has low power requirements, uses relatively unsophisticated electronics, and is capable of withstanding large gas pressures and accelerations. The system uses a one-piece fin assembly which is de-spun so that its guidance fins maintain a constant attitude with respect to the ground. The guidance fins and their hub can be nutated simultaneously and independently in two orthogonal planes by pivoting and translating a single control rod. The hub cooperates with the projectile body to reduce its base drag and thereby extend its range.

REFERENCES:
patent: 3104081 (1963-10-01), Arnett
patent: 3135484 (1964-06-01), Herrmann
patent: 3291418 (1966-12-01), Brunk et al.
patent: 3603533 (1971-09-01), Stripling
patent: 3790103 (1974-02-01), Peoples
patent: 3952970 (1976-04-01), Orzechowski et al.
patent: 4076187 (1978-02-01), Metz
patent: 4373688 (1983-02-01), Topliffe
patent: 4426048 (1984-01-01), Mildren
patent: 4438893 (1984-03-01), Sands et al.

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