Wing load alleviation system using tabbed allerons

Aeronautics and astronautics – Aircraft control

Patent

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244 90R, B64C 910

Patent

active

044796200

ABSTRACT:
A wing load alleviation system for redistributing aircraft loads encountered during flight by symmetrically deflecting the outboard ailerons of the aircraft includes a trailing edge tab pivotally supported on each outboard aileron. As each outboard aileron is deflected by the wing load alleviation system to reduce wing bending moments, the corresponding tab is deflected in aerodynamic opposition thereto so as to reduce wing torsional loads caused by the deflection of its associated outboard aileron. The span of each tab is equal to or less than that of its associated outboard aileron, and the chord of each tab is a predetermined fraction of that of its associated outboard aileron. Each tab may be mechanically linked to its associated outboard aileron so that deflection of the outboard aileron causes a proportional but opposite deflection of the tab.

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