Aircraft Wing Flap Support Linkage With Dual Over-Center Positions
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing flap support mechanisms in aircraft wings exert high actuation loads on actuators due to reliance on a single over-center position during flap deployment, leading to increased mechanical stress and power requirements.
Innovation Solution
A flap support system with two over-center positions, one for the stowed and one for the fully deployed position, utilizing a crank, drive link, flap link, and rocker bracket configuration to distribute loads into the fixed wing structure, reducing actuator loads and power requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single over-center position mechanism is used during flap deployment, then the mechanism is simpler, but actuator loads become excessively high
Solution Approach 1:
The mechanism is divided into two separate over-center position systems: one for the stowed position and one for the fully deployed position. This segmentation allows the actuator loads to be distributed and reduced at each position rather than concentrated at a single point, resolving the contradiction between mechanism simplicity and actuator load reduction.
2Device complexity
If a single over-center position mechanism is used, then the structure is simpler, but power requirements increase
Solution Approach 1:
The power requirement is segmented across two distinct over-center positions rather than one. By distributing the mechanical advantage across two positions, the peak power demand on the actuator is reduced, resolving the contradiction between structural simplicity and power consumption.
3Use of energy by moving object
If actuator loads are reduced, then power requirements decrease, but the mechanism becomes more complex
Solution Approach 1:
The mechanism dynamically transitions through two over-center positions during flap deployment, with each position providing mechanical advantage at different stages. This dynamic approach reduces actuator power requirements while maintaining reasonable mechanism complexity through the use of standard linkage components.
Data Source
AI summary
A system and a method include a crank pivotally coupled to a bracket of a main body of a wing of an aircraft. A drive link is pivotally coupled to the crank. A flap link is pivotally coupled to a carrier beam extending from a flap moveably coupled to the main body of the wing. A rocker bracket is pivotally coupled to the flap link and the drive link.