Flap actuation system with support catcher link
Abstract:
A flap actuation system employed in an aircraft wing with a flap having an internal structure employs a drive link pivotally attached at a top end with a drive axle to a forward lug on the internal structure and pivotally attached at a bottom end with a first pivot axle to a flap support element. An actuator is operably coupled to the drive link intermediate the top end and bottom end. A trailing link is pivotally attached at a leading end with a second pivot axle to the flap support element and pivotally attached at a trailing end with a reaction axle to an aft fitting on the internal structure. A catcher link is pivotally attached at a bottom end to the flap support element and at a top end to an intermediate fitting engaged to the internal structure. The catcher link is unloaded in a typical operating condition and upon a failure in the drive link, first pivot axle, drive axle, forward lug, trailing link, second pivot axle, reaction axle or aft fitting a load is induced on the catcher link to accommodate the failure condition.
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