Lateral Linkage Assembly for Aircraft Wing Hinged Panels
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Solution Overview
Problem
Existing linkage assemblies for aircraft wing hinged panels consume significant vertical space, requiring thicker wings and reducing flight efficiency due to their vertical orientation and long linkage components, which is not suitable for thinner, lighter wings.
Innovation Solution
A linkage assembly with a flap follower arm, rocker, cross-bar link, and panel link that moves in a more lateral direction, allowing the hinged panel to be slaved to the flap's motion without needing extensive vertical space, utilizing a swivel tie rod and panel link to rotate the hinged panel downward as the flap deploys.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If existing linkage assemblies use vertical orientation and long linkage components, then the hinged panel can be coupled to the flap, but significant vertical space is consumed requiring thicker wings
Solution Approach 1:
The linkage assembly transitions from a vertical orientation to a lateral orientation, moving components in the spanwise direction (inboard/outboard) rather than vertically. This dimensional change allows the linkage to achieve the same functional coupling between flap and hinged panel while consuming significantly less vertical space within the wing cross-section.
Solution Approach 2:
The linkage assembly is divided into multiple interconnected components (flap follower arm, rocker, cross-bar link, panel link) that work together in a coordinated sequence. This segmentation allows each component to perform a specific function while collectively achieving the motion transfer from flap to hinged panel with reduced vertical space requirements.
2Reliability
If existing linkage assemblies use long linkage components, then the hinged panel can be slaved to flap motion, but the structure becomes heavier and less efficient
Solution Approach 1:
By reorienting the linkage components laterally instead of vertically, the effective length of linkage components is reduced. This dimensional change maintains the functional reliability of motion coordination while decreasing the amount of material required, thereby reducing the weight of the moving linkage assembly.
3Ease of operation
If existing linkage assemblies consume significant vertical space, then the hinged panel can be positioned correctly, but thinner wings cannot be used
Solution Approach 1:
The linkage assembly achieves hinged panel positioning by utilizing lateral motion (inboard/outboard direction) rather than vertical motion. This allows correct positioning of the hinged panel relative to the flap while consuming minimal vertical space, thereby enabling use in thinner wings and providing greater wing design flexibility.
Data Source
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AI summary
Linkage assemblies for aircraft wing hinged panels are described herein. An example linkage assembly (300) includes a flap follower arm (312) coupled between a spoiler support beam (302) and a flap (202), a rocker (340), a panel link (338) coupled between the hinged panel and the rocker, and a cross-bar link (342) coupled between the flap follower arm and the rocker. The flap follower arm, the rocker, the panel link, and the cross-bar link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other.