Aircraft Wing Tip Actuation Linkage Design
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Solution Overview
Problem
Existing aircraft wing designs with foldable wing tips face challenges in reducing complexity and weight of the actuation unit while maintaining efficient load transfer and avoiding penetration of the outer wing skin.
Innovation Solution
The use of a link and two linear actuators, mounted via multiple hinges, allows for efficient kinematics in transferring actuation loads to the foldable wing tip portion, reducing the complexity and weight of the actuation unit and keeping it entirely within the wing's outer contour.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a traditional actuation unit is used to move the foldable wing tip portion, then the wing tip can be moved between extended and folded positions, but the actuation unit increases in weight and complexity
Solution Approach 1:
The actuation unit is segmented into two separate linear actuators (first and second linear actuators) that work independently but coordinate through a common link. This segmentation allows each actuator to be smaller and simpler, while the distributed hinge arrangement (second, third, fourth, fifth, and sixth hinges) further divides the mechanical function across multiple connection points, reducing the complexity of any single component.
Solution Approach 2:
The actuation mechanism transitions from a single-plane rotation about the first hinge axis to a multi-dimensional linkage system. The link connects multiple hinges that are spaced apart along the first hinge axis, creating a planar linkage mechanism that operates in two dimensions. This dimensional expansion allows the actuation unit to achieve the same rotational effect while distributing mechanical loads across multiple points, thereby reducing individual component complexity.
2Ease of operation
If a traditional actuation unit is used to move the foldable wing tip portion, then the wing tip can be moved between extended and folded positions, but the actuation unit weight increases
Solution Approach 1:
The actuation unit is segmented into two separate linear actuators (first and second linear actuators) that work independently but coordinate through a common link. This segmentation allows each actuator to be smaller and simpler, while the distributed hinge arrangement (second, third, fourth, fifth, and sixth hinges) further divides the mechanical function across multiple connection points, reducing the complexity of any single component.
Solution Approach 2:
The actuation mechanism transitions from a single-plane rotation about the first hinge axis to a multi-dimensional linkage system. The link connects multiple hinges that are spaced apart along the first hinge axis, creating a planar linkage mechanism that operates in two dimensions. This dimensional expansion allows the actuation unit to achieve the same rotational effect while distributing mechanical loads across multiple points, thereby reducing individual component complexity.
3Device complexity
If the actuation unit is designed to be lightweight and simple, then weight and complexity are reduced, but the ability to transfer actuation loads efficiently may be compromised
Solution Approach 1:
The patent merges the functions of multiple hinges and actuation mechanisms into a unified planar linkage system. The link connects the second, third, fourth, fifth, and sixth hinges into a single integrated structure that simultaneously transfers actuation forces from both linear actuators to the foldable wing tip portion. This merging ensures that actuation loads are efficiently distributed and transferred across the entire linkage mechanism, maintaining force transfer capability while keeping the overall design simple.
Solution Approach 2:
The link acts as an intermediary element that mediates between the two linear actuators and the foldable wing tip portion. It receives actuation forces from both actuators through the distributed hinge connections and combines these forces to produce the rotational movement of the wing tip portion about the first hinge axis. This intermediary role allows the system to maintain efficient load transfer while using simpler, lighter components.
4Object-affected harmful factors
If the actuation unit is placed inside the outer contour of the wing, then aerodynamics and structural integrity are optimized, but the available space for mounting components is limited
Solution Approach 1:
The actuation unit is segmented into two separate linear actuators (first and second linear actuators) that work independently but coordinate through a common link. This segmentation allows each actuator to be smaller and simpler, while the distributed hinge arrangement (second, third, fourth, fifth, and sixth hinges) further divides the mechanical function across multiple connection points, reducing the complexity of any single component.
Solution Approach 2:
The actuation mechanism transitions from a single-plane rotation about the first hinge axis to a multi-dimensional linkage system. The link connects multiple hinges that are spaced apart along the first hinge axis, creating a planar linkage mechanism that operates in two dimensions. This dimensional expansion allows the actuation unit to achieve the same rotational effect while distributing mechanical loads across multiple points, thereby reducing individual component complexity.
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 configuration enables a compact and lightweight actuation system that efficiently moves the foldable wing tip between extended and folded positions without penetrating the wing's outer skin, optimizing aerodynamics and structural integrity.
Implementation Method 1
The first linear actuator, preferably at its first end, is rotatably mounted to the fixed wing via a third hinge spaced apart from the second hinge, and preferably at its opposite second end, is rotatably mounted to the link, preferably to the second end of the link, via a fourth hinge spaced apart from the second hinge. Preferably, the first linear actuator is formed as a hydraulic actuator, a pneumatic actuator, or an electromagnetic linear motor
Implementation Method 2
The second linear actuator, preferably at its first end, is rotatably mounted to the foldable wing tip portion via a fifth hinge, and preferably at its opposite second end, is rotatably mounted to the link, preferably to the second end of the link, via a sixth hinge spaced apart from the second hinge. Preferably, the second linear actuator is formed as a hydraulic actuator, a pneumatic actuator, or an electromagnetic linear motor
Implementation Method 3
The link is rotatably mounted to the fixed wing via a second hinge, preferably at its first end. The first linear actuator... is rotatably mounted to the link... via a fourth hinge spaced apart from the second hinge... The second linear actuator... is rotatably mounted to the link... via a sixth hinge spaced apart from the second hinge
Data Source
AI summary
A wing for an aircraft, comprising a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatably about a first hinge axis between an extended and folded positions, and an actuation unit to actuate the foldable wing tip portion for movement about the first hinge axis. The actuation unit comprises a link, a first and a second linear actuator. The link is rotatably mounted to the fixed wing via a second hinge, the first linear actuator is rotatably mounted to the fixed wing via a third hinge spaced from the second hinge, and is rotatably mounted to the link via a fourth hinge spaced from the second hinge. The second linear actuator is rotatably mounted to the foldable wing tip portion via a fifth hinge, and is rotatably mounted to the link via a sixth hinge spaced from the second hinge.