Foldable Wing Hinge Pin Structure for Stable Load Distribution
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Solution Overview
Problem
Existing foldable aircraft wing mechanisms are limited in their ability to efficiently manage wing span reduction and do not effectively distribute loads during folding, leading to gaps between wing sections and potential structural issues.
Innovation Solution
The use of hinge pins with a first and second flange spaced apart along a central axis, and a through hole to receive a drive shaft, which stabilizes the hinge pin joint under single-shear loading and allows the foldable tip to rotate relative to the fixed structure, reducing non-uniform load distributions and enabling folding without in-flight loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a simple hinge connection is used to enable folding, then the ease of operation is improved, but the structural strength and load distribution deteriorate
Solution Approach 1:
The hinge pin is divided into multiple functional segments: a first flange for connecting to the foldable tip, a second flange for connecting to the fixed structure, and a shaft portion with a through hole for the drive shaft. This segmentation allows each part to perform its specific function optimally while working together to provide both folding capability and structural strength.
Solution Approach 2:
The hinge pin extends in multiple dimensions: the first and second flanges are spaced apart along the central axis (providing rotational freedom for folding), while the flanges themselves have extended surfaces that distribute loads in perpendicular directions. This multi-dimensional structure simultaneously enables folding motion and provides robust load distribution.
2Ease of operation
If the flanges are spaced apart to allow rotation, then the ease of operation is improved, but the stability under load deteriorates
Solution Approach 1:
The shaft portion of the hinge pin acts as an intermediary element between the first and second flanges. It maintains the spaced-apart configuration that allows rotation while providing structural continuity that ensures joint stability under load. The through hole in the shaft portion further mediates the connection to the drive shaft, coordinating both rotational freedom and load-bearing stability.
3Strength
If a robust hinge structure is used to maintain stability, then the structural strength is improved, but the device complexity increases
Solution Approach 1:
The hinge pin is designed as a multi-functional universal component: the first and second flanges provide both rotational freedom for folding operations and load-bearing surfaces for structural stability. The shaft portion with the through hole simultaneously maintains flange spacing, provides structural continuity, and accommodates the drive shaft connection. This universality achieves robust stability without increasing device complexity.
Data Source
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AI summary
Hinge pins for foldable aircraft wings are described. An example apparatus includes a hinge pin (500) to rotatably couple a foldable tip of an aircraft wing to a fixed structure of the aircraft wing. The hinge pin includes a first flange (526), a second flange (528) spaced apart from the first flange (526) along a central axis (524) of the hinge pin (500), and a through hole (532) oriented along the central axis (524).