Kinked Link Support for Aircraft Trailing Edge Panels
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Solution Overview
Problem
Existing aircraft wing designs face challenges in supporting trailing edge panels efficiently while minimizing space and avoiding clashes with mechanical and electrical systems, particularly in the limited space behind the rear spar, and require innovative support structures that allow for easy installation and removal of routings without obstructing airflow or causing damage during over-travel failures.
Innovation Solution
The implementation of a kinked link support structure with pivotally attached arms that connect to the trailing edge panel and a fairing, allowing for rotation and deflection, which enables the routings to be installed or removed transversely to their length, reducing space usage and minimizing the risk of damage from spoiler over-travel.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a conventional support structure is used for the trailing edge panel, then the panel is supported, but it obstructs airflow and occupies valuable space behind the rear spar
Solution Approach 1:
The support structure uses a kinked link with pivot joints that allow dynamic movement. The link can rotate and deflect to accommodate routing installation/removal while maintaining panel support, and returns to its original position to minimize airflow obstruction during flight operations
Solution Approach 2:
The kinked link structure introduces rotational freedom in addition to the conventional linear support arrangement. By allowing movement in multiple dimensions (rotation about pivot axes, deflection), the structure can clear airflow paths while maintaining structural support function
2Strength
If a fixed support structure is used for the trailing edge panel, then the panel is securely supported, but it prevents easy installation and removal of routings
Solution Approach 1:
The pivot joints in the kinked link structure allow the support arms to rotate and move out of the way during routing installation, then return to their support position after routing is installed. This dynamic capability enables easy routing maintenance while maintaining secure panel support
Solution Approach 2:
The support structure is divided into multiple arms connected by pivot joints, allowing each segment to move independently. This segmentation enables the structure to be manipulated during routing installation while maintaining overall structural integrity for panel support
3Volume of stationary object
If the support structure is positioned to maximize fuel tank volume, then fuel capacity is increased, but the risk of damage from spoiler over-travel increases
Solution Approach 1:
The kinked link structure is designed to deflect and absorb energy before spoiler over-travel can cause damage. The pivot joints allow controlled movement that cushions the impact, protecting the trailing edge panel and support structure from damage during over-travel failures
Solution Approach 2:
The kinked link acts as an intermediary element between the trailing edge panel and the spoiler support structure. It provides a compliant connection that allows movement and absorbs energy, mediating between the panel support function and the spoiler over-travel hazard
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
This solution provides a compact, low-profile support arrangement that allows for efficient installation and removal of routings without obstructing airflow, reduces the risk of damage during spoiler over-travel, and maintains the structural integrity of the wing while maximizing fuel tank volume and aerodynamic performance.
Implementation Method 1
the first pivot joint is configured to permit rotation about a first pivot axis, and the second pivot joint is configured to permit rotation about a second pivot axis which is preferably substantially parallel with the first pivot axis
Implementation Method 2
the first arm of the kinked link is pivotally attached to the trailing edge panel at a first pivot joint, and the second arm of the kinked link is pivotally attached to the support structure at a second pivot joint
Data Source
AI summary
An aircraft wing including a wingbox with an upper cover, a lower cover, a forward spar and a rear spar. A leading edge of a trailing edge panel is attached to the wingbox. A support structure is attached to the wingbox. A kinked link includes a first arm, a second arm, and a corner where the first and second arms meet. The first arm of the kinked link is pivotally attached to the trailing edge panel at a first pivot joint, and the second arm of the kinked link is pivotally attached to the support structure at a second pivot joint.