Morphing Airfoil Using Segmented Beams and Flexible Skin
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Solution Overview
Problem
Conventional movable wing parts in aircrafts require complex and heavy structures, leading to early air separation, reduced lift, increased drag, and noise due to their high part-count and maintenance needs, while existing morphing wing structures often have sharp edges and small radii of curvature, which are not aerodynamically optimal.
Innovation Solution
An airfoil-shaped body with a variable outer profile is achieved through a system of beam sections and a joining member with a hollow profile, allowing for curvature alteration and flexibility without the need for complex structures, using actuators to pivot the beam sections and deform the joining member, which is made of materials like thermoplastic composite fiber materials for reduced fatigue and increased flexibility.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional movable wing parts are used, then the wing can change shape, but the structure becomes heavy and complex with high part-count
Solution Approach 1:
The wing structure is divided into multiple beam sections (first beam section, second beam section) that can move relative to each other. The joining member connects these segments and enables shape change through localized movement, reducing the complexity of moving the entire wing structure.
Solution Approach 2:
The skin is designed as a flexible covering that spans between the beam sections. When the beam sections move relative to each other, the skin flexes to accommodate the shape change, maintaining a smooth aerodynamic surface without requiring complex mechanical linkages throughout the entire wing.
2Adaptability or versatility
If movable wing parts are deflected, then shape control is achieved, but the local radius of curvature becomes small causing early air separation
Solution Approach 1:
The design maintains a large local radius of curvature at the junction between beam sections by using a curved joining member and flexible skin. This gradual curvature transition prevents sharp edges that would cause early air separation, while still enabling effective shape control for lift and drag management.
3Adaptability or versatility
If movable wing parts are used, then shape variation is possible, but maintenance interval becomes frequent
Solution Approach 1:
The flexible skin automatically adjusts and seals itself as the beam sections move relative to each other, maintaining aerodynamic continuity without requiring complex sealing mechanisms or frequent maintenance. The elastic deformation of the joining member and skin creates a self-accommodating system that reduces wear and maintenance needs.
4Adaptability or versatility
If complex movable structures are used, then shape control is achieved, but weight increases
Solution Approach 1:
By segmenting the wing into beam sections connected by a lightweight joining member, the system achieves shape control with minimal mass. The segmented approach allows localized movement rather than requiring a heavy, fully-mechanized movable structure.
Solution Approach 2:
The flexible skin acts as a lightweight structural element that provides both aerodynamic surface and structural connectivity between beam sections. This eliminates the need for heavy mechanical linkages, hinges, and actuators that would be required in a rigid movable wing structure.
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 enhances lift, reduces drag, and minimizes noise by maintaining a smooth aerodynamic surface with a gradual curvature, allowing for efficient airflow and flexible shape variation without the need for sharp edges or complex structures, thus improving the aerodynamic performance and reducing maintenance needs.
Implementation Method 1
The joining member is adapted to allow relative movement between said beam sections by an elastic deformation of the joining member
Data Source
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AI summary
An airfoil-shaped body having a variable outer shape, comprising: a first skin, defining a suction surface, a second skin, defining a pressure surface and connected to the first skin at least at a leading edge and/or a trailing edge of the airfoil-shaped body, at least one elongate stiffening beam, arranged inside a cavity of the airfoil-shaped body and secured to at least one of said first and second skins, the stiffening beam including at least a first and a second beam section arranged one after the other and a joining member, arranged between end portions of the beam sections and connected thereto, said joining member being adapted to allow relative movement between the beam sections by an elastic deformation; and an actuator that is operationally associated with said elongate stiffening beam, wherein, upon operating the actuator, the first beam section is moved with respect to the second beam section, or vice versa, changing the orientation of the beam sections with respect to each other, which causes a change in the variable outer shape of the airfoil-shaped body.