Variable camber leading edge airfoil system

Details Variable camber leading edge airfoil system Variable camber leading edge airfoil system

1975-08-25

1977-08-09

Blix, Trygve M.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

B64C 348

Patent

active

040405796

ABSTRACT:
A variable camber leading edge airfoil system that is attached to the front f the fixed wing section of an aircraft. When the system is in the retracted position it provides an airfoil having a slight curvature suitable for supersonic flight and when in the extended position it provides an airfoil having a large curvature suitable for high lift subsonic flight. The system is capable of operating at any intermediate position depending upon the requirements of any particular flight conditions. The system includes a rigid lower panel, a leading edge beam, a flexible upper panel and an actuating mechanism. Actuation of the actuating mechanism to the extended position simultaneously causes the rigid lower panel to move downward and rotate counterclockwise, the leading edge beam to move downward and rotate counterclockwise, and causes the flexible upper panel to flex to a proper curvature and have the rearward edge move forward and slide along the upper forward edge of the fixed wing section.

REFERENCES:
patent: 1868748 (1932-07-01), Hogan
patent: 3504870 (1970-04-01), Cole et al.
patent: 3716209 (1973-02-01), Pierce
patent: 3836099 (1974-09-01), O'Neill et al.
patent: 3941334 (1976-03-01), Cole

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