Invention Grant
- Patent Title: Flap actuation system with support catcher link
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Application No.: US16441426Application Date: 2019-06-14
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Publication No.: US11312474B2Publication Date: 2022-04-26
- Inventor: Kevin R. Tsai , Miranda Peterson
- Applicant: The Boeing Company
- Applicant Address: US IL Chicago
- Assignee: The Boeing Company
- Current Assignee: The Boeing Company
- Current Assignee Address: US IL Chicago
- Agent Felix L. Fischer
- Main IPC: B64C9/02
- IPC: B64C9/02 ; B64C9/18

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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