Aircraft Wing Foldable Tip Actuation Linkage
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing foldable wing designs for aircraft require complex and heavy actuation units that often penetrate the wing's outer skin, increasing weight and cost while compromising aerodynamics and structural integrity.
Innovation Solution
A five-bar-linkage actuation system with a linear actuator is integrated entirely within the wing's outer contour, using a linkage of link elements and hinges to transfer loads efficiently, reducing complexity and weight, and allowing the foldable wing tip to move between extended and folded positions without penetrating the wing's skin.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a complex actuation unit is used to move the foldable wing tip portion, then the reliability of movement between extended and folded positions is improved, but the weight and complexity of the actuation unit increases
Solution Approach 1:
The actuation unit is segmented into multiple independent link elements (first link element, second link element) connected by hinges, rather than using a single complex actuator. This segmentation allows each component to be simpler while collectively achieving the required reliable movement function.
Solution Approach 2:
The linkage system uses dynamic hinge connections that allow rotational movement between link elements, creating an adaptable mechanism that can reliably transition between positions while maintaining structural integrity. The dynamic nature of the hinge connections provides inherent movement control and reliability.
2Reliability
If a complex actuation unit is used to move the foldable wing tip portion, then the reliability of movement between extended and folded positions is improved, but the weight of the actuation unit increases
Solution Approach 1:
The actuation unit is divided into multiple lightweight link elements rather than using a single heavy actuator. Each link element can be optimized for minimal weight while maintaining strength, and the distributed mass reduces overall weight compared to a centralized complex actuation system.
Solution Approach 2:
The linkage system acts as an intermediary mechanism between the actuation force and the wing tip portion, using mechanical advantage through the hinge connections to reduce the weight of the actuation unit while maintaining reliable movement capability.
3Ease of manufacture
If the actuation unit penetrates the outer skin of the wing, then the ease of installation and maintenance is improved, but the aerodynamic performance and structural integrity deteriorate
Solution Approach 1:
The entire actuation unit and linkage system are nested within the wing's outer contour, with all link elements and hinges contained inside the wing structure. This nesting eliminates the need for penetrations while maintaining ease of installation through internal integration.
Solution Approach 2:
The linkage system is arranged in a three-dimensional configuration within the wing's thickness dimension, allowing the actuation mechanism to operate internally without requiring external penetrations. The spatial arrangement of link elements in multiple dimensions enables functional access through the wing structure.
4Ease of manufacture
If the actuation unit penetrates the outer skin of the wing, then the ease of installation and maintenance is improved, but the structural integrity of the wing deteriorates
Solution Approach 1:
The actuation unit is completely nested within the wing's structural boundaries, eliminating penetrations that would compromise structural integrity. The linkage elements are positioned within the wing's internal volume, preserving the continuity and strength of the outer skin and structural framework.
Solution Approach 2:
The actuation mechanism operates in the internal three-dimensional space of the wing, using the wing's thickness and internal volume to accommodate the linkage system without compromising the external structural shell. This dimensional arrangement maintains structural integrity while enabling actuation functionality.
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 design reduces the actuation unit's complexity and weight, maintaining aerodynamic and structural integrity by keeping the linkage and actuation unit inside the wing's contour, minimizing weight and cost while enabling smooth folding and extension of the wing tip.
Implementation Method 1
The linear actuator might be a length adjustable link or rod, such as a hydraulic or pneumatic cylinder or an electromagnetic linear motor
Implementation Method 2
The linear actuator might be a length adjustable link or rod, such as a hydraulic or pneumatic cylinder or an electromagnetic linear motor
Data Source
AI summary
A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatable about a first hinge axis between an extended position and a folded position, and an actuation unit for actuating the foldable wing tip portion for movement about the first hinge axis. A wing having an actuation unit with reduced complexity and weight and that is arranged entirely inside the outer contour of the wing is disclosed in which the actuation unit is arranged at one of the fixed wing and the foldable wing tip portion and is coupled to the other of the fixed wing and the foldable wing tip portion via a linkage. The linkage includes a first link element and a second link element, wherein the first link element is rotatably mounted to the one of the fixed wing and the foldable wing tip portion via a second hinge and is rotatably coupled to the second link element via a third hinge.