Foldable Wing Tip Device Using Euler Axis Rotation
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Solution Overview
Problem
Existing aircraft folding wing designs require secondary structures to avoid clashing and often necessitate redesigning internal layouts to accommodate essential structures, limiting flexibility and increasing complexity.
Innovation Solution
A method involving the use of an Euler axis of rotation and a cut plane, oriented normal to each other, to design a foldable wing tip device that reduces span during ground operations without clashing, allowing for optimized integration and reduced actuation loads, while minimizing interference with internal systems and structures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If a folding wing design is implemented to reduce span during ground operations, then the aircraft can meet airport clearance requirements, but secondary structures are required to avoid clashing between inner and outer wing parts
Solution Approach 1:
The wing is divided into two distinct segments: a fixed inner wing portion and a movable outer wing tip device. This segmentation allows the outer portion to be independently rotated about the Euler axis to reduce span during ground operations while the inner portion remains stationary, eliminating the need for secondary structures to avoid clashing.
Solution Approach 2:
The rotation of the wing tip device occurs about an Euler axis that is oriented at a compound angle (not parallel to any principal axis), introducing a three-dimensional rotation that simultaneously achieves span reduction while maintaining clearance from the fuselage and avoiding interference with internal structures.
2Length of moving object
If the wing junction is designed to accommodate folding mechanisms, then span reduction is achieved, but wing volume in the vicinity of the junction is limited
Solution Approach 1:
By segmenting the wing into fixed and movable portions separated by a cut plane perpendicular to the Euler axis, the design preserves the full volume of the fixed wing portion while the movable tip device rotates outside this volume, avoiding interference with internal structures.
Solution Approach 2:
The Euler axis is oriented at a compound angle that positions the rotation path of the wing tip device in three-dimensional space such that it clears the fuselage and internal structures, effectively utilizing spatial volume that would otherwise be unavailable in conventional folding designs.
3Length of moving object
If conventional folding wing designs are used, then span reduction is achieved, but the internal layout must be significantly redesigned and actuation loads increase
Solution Approach 1:
The cut plane is predetermined to be perpendicular to the Euler axis before finalizing the internal layout. This preliminary definition of the separation plane allows internal structures to be designed and positioned in the fixed wing portion without needing to accommodate the complex movements required in conventional folding designs, simplifying the integration process.
Solution Approach 2:
By using a compound angle Euler axis rather than a conventional horizontal or vertical rotation axis, the design creates a rotation path that naturally clears internal structures and fuselage components, eliminating the need for significant redesign of the internal layout while reducing actuation loads through optimized mechanical advantage.
Data Source
AI summary
A method of manufacturing a foldable aerodynamic structure, such as a wing, for an aircraft. The wing (1) including an inner region (1) and an outer region (3) rotatable relative to the inner region between a flight configuration and a ground configuration. The method includes designing the foldable aerodynamic structure by determining the location and orientation of an Euler axis of rotation (11) about which the outer region rotates to achieve the ground configuration and determining a cut plane (13), perpendicular to that Euler axis, separating the inner and outer regions; and iteratively repeating this process until a preferred cut plane (13) is obtained that satisfies at least one design criteria.