Aircraft Wing Edge Support Assembly with Spherical Bearing
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Solution Overview
Problem
Existing support assemblies for aircraft wing leading and trailing edge devices are bulky and inefficient, occupying valuable space within the wing structure while failing to provide adequate support throughout the entire range of movement, especially in larger aircraft where space is limited and weight, manufacturing costs, and complexity are concerns.
Innovation Solution
A support assembly comprising a fixed support member, an intermediate link arm pivotally mounted to the support member, and a primary link arm with a bearing element allowing the wing leading or trailing edge device to move relative to the link arms in any direction during deployment and retraction, utilizing a part-spherical bearing to enable pivoting and angular movement, thereby optimizing space usage and support efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a swinging track design with multiple components is used to support the flap, then the flap can follow a three-dimensional path during deployment, but the assembly occupies excessive space within the wing structure
Solution Approach 1:
The patent combines multiple support components (swinging arm, guide track, roller carriage, bearing) into a single integrated spherical bearing assembly. This merging of functions allows the flap to achieve three-dimensional movement capability while occupying minimal space within the wing structure, directly resolving the contradiction between adaptability and volume.
Solution Approach 2:
The spherical bearing assembly serves multiple functions simultaneously: it acts as a pivot point for rotation, a guide for arcuate movement, and a support for the flap rib. This multi-functionality eliminates the need for separate swinging arms and guide tracks, reducing the overall space required while maintaining full three-dimensional movement capability.
2Adaptability or versatility
If a swinging track design with multiple components is used to support the flap, then the flap can follow a three-dimensional path during deployment, but the manufacturing costs and complexities increase
Solution Approach 1:
The patent merges multiple discrete components (swinging arm, guide track, roller carriage, bearing) into a single spherical bearing assembly. This integration dramatically reduces the number of parts that need to be manufactured and assembled, thereby reducing manufacturing complexity and costs while preserving the three-dimensional movement capability.
Solution Approach 2:
The spherical bearing assembly performs multiple functions that previously required separate components: it provides rotational pivoting, guides arcuate movement, and supports the flap rib. This multi-functionality simplifies the overall device structure and reduces manufacturing complexity.
3Weight of moving object
If a compact support assembly is used to minimize space, then weight is reduced, but support capability throughout the entire range of movement may be compromised
Solution Approach 1:
The spherical bearing assembly is designed to perform multiple support functions simultaneously, ensuring reliable support throughout the entire range of motion. The spherical geometry naturally guides the flap through its required arcuate path while allowing free rotation, maintaining reliability without requiring additional heavy components.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution provides a lightweight, robust, and space-efficient support assembly that allows wing edge devices to move freely in three dimensions, reducing weight and manufacturing complexity while maintaining effective support throughout their range of motion.
Implementation Method 1
an intermediate link arm having one end pivotally mounted to the support member for rotation relative to the support member about a first axis
Implementation Method 2
a primary link arm having a first end attached to the opposite end of the intermediate link arm via a bearing element so that the primary link arm, together with a wing leading or trailing edge device attached to the second end of the primary link arm, can move relative to the intermediate link arm in any direction
Data Source
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AI summary
An assembly (10) to support a wing leading or trailing edge device during deployment and retraction of said wing leading or trailing edge device from a wing of an aircraft is disclosed. The assembly comprises a fixed support member (15) attachable to the support structure of an aircraft wing, an intermediate link arm (22) having one end pivotally mounted to the support member (15) for rotation relative to the support member about a first axis (A-A) and, a primary link arm (30) having a first end pivotally mounted to the opposite end of the intermediate link arm (22) for rotation relative to the intermediate link arm (22) about a second axis (B-B). A second end of the primary link arm (30) is configured for attachment to a wing leading or trailing edge device (11) via a bearing element so that the wing leading or trailing edge device (11) can move relative to the primary link arm (30) in any direction when the intermediate (22) and primary (30) link arms rotate about said first (A-A) and second (B-B) axes, respectively, during deployment or retraction of said wing leading or trailing edge device (11) from an aircraft wing.