Aerodynamic spin control device for aircraft

Aeronautics and astronautics – Aircraft control – Automatic

Patent

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Details

244 45A, B64C 1700

Patent

active

040158004

ABSTRACT:
An aerodynamic spin control device or apparatus is provided for high speed aircraft for effecting inherent aerodynamic spin resistance and/or automatic spin recovery for the aircraft. In one embodiment clam shell doors or like devices are pivotably mounted individually and symmetrically at their forward ends in the forebody area of the aircraft so as to be automatically deployable outwardly in response to spin created forces, whereby to change the fuselage yawing moment from pro-spin to anti-spin by changing the flow field over the fuselage forebody at high angles of attack, by effectively changing the geometric characteristics of the forebody. The doors, in their housed or undeployed positions, conform to the normal contour of the forebody of the aircraft and can be armed (i.e. unlocked) manually or automatically. When unlocked, the doors would extend until the centrifugal and aerodynamic forces acting on the doors are in balance. Tether lines, however, are connected to the inside of the doors to limit the outward angular movement of the doors upon deployment to an optimum angle. Weights may be attached to the inside of the doors to ensure automatic deployment in response to low angular accelerations and velocities that might be experienced during the incipient spin motion. As the spin is terminated, aerodynamic forces return the doors to their housed position.

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patent: 3273834 (1966-09-01), Bower
patent: 3578796 (1971-05-01), Hagler et al.
patent: 3642234 (1972-02-01), Kamber et al.

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