Variable twist leading edge flap

Details Variable twist leading edge flap Variable twist leading edge flap

1978-01-23

1980-02-19

Kelmachter, Barry L.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

B64C 354

Patent

active

041891210

ABSTRACT:
A leading edge flap system for the tapered wing of an aircraft and more particularly, the spanwise flap segments and their linkage mechanism allow a relatively large leading edge bullnose member to be extended and unfolded out from a wing cavity. Each of the spanwise flap segments is supported from the leading edge of the wing by a pair of linkage mechanisms which are spaced apart spanwise and attached towards each spanwise end portion of the flap segment. The spanwise spaced apart linkage mechanisms are interconnected by a torque tube which is rotated through a fixed number of degrees by an actuator. By altering the geometry of the linkage mechanism, a differential motion is applied between the spanwise ends of the flap segment to torsionally twist the panel in a spanwise direction thereby varying the flap deflection angle spanwise.

REFERENCES:
patent: 3504870 (1970-04-01), Cole et al.
patent: 3638886 (1972-02-01), Zimmer
patent: 3910530 (1975-10-01), James et al.

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