Flexible Transition Piece for Aircraft Control Surface Gap Sealing
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Solution Overview
Problem
Conventional aircraft flaps and control surfaces suffer from efficiency losses and noise generation due to gaps, which also lead to radar signature issues, as air flows through and surface waves are emitted, particularly in military applications.
Innovation Solution
A shape-variable, flexible transition piece with intersecting ribs and a shear-compliant outer skin, such as a biaxially woven metal mesh or elastomer layer, is mounted between structural components to form a continuous surface, allowing for deformation and reducing gaps between flaps and control surfaces, thereby enhancing aerodynamics and reducing radar emission.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional flaps and control surfaces are used with gaps, then the structure is simple and easy to manufacture, but air flows through the gaps reducing efficiency and generating noise and radar emissions
Solution Approach 1:
The patent employs a flexible transition piece comprising a thin-walled tubular structure that can deform to maintain a continuous surface between the flap and control surface. This flexible shell approach eliminates gaps without requiring rigid complex mechanisms, thus improving aerodynamic efficiency while reducing noise and radar emissions generated by gap airflow
Solution Approach 2:
The transition piece is designed with dynamic deformation capability, allowing it to adapt its shape as the flap moves between extended and retracted positions. This dynamic adjustment ensures continuous surface coverage throughout the motion range, preventing air leakage and maintaining efficiency without compromising structural simplicity
2Productivity
If a transition piece is introduced to cover gaps and form a continuous surface, then aerodynamic efficiency improves and noise is reduced, but device complexity increases
Solution Approach 1:
The transition piece utilizes a thin-walled tubular structure that achieves gap closure through material flexibility rather than complex mechanical assemblies. This flexible shell design forms a continuous aerodynamic surface while maintaining relative structural simplicity, avoiding the need for multiple rigid components and complex actuation mechanisms
Solution Approach 2:
The transition piece is designed to deform automatically in response to flap position changes without requiring external actuation. The self-service mechanism relies on the inherent flexibility of the thin-walled structure to adapt to varying gap conditions, reducing complexity by eliminating additional control systems
3Strength
If the transition piece is made rigid to maintain structural integrity against air loads, then strength is improved, but flexibility to accommodate angle changes is reduced
Solution Approach 1:
The transition piece employs dynamic structural characteristics, remaining flexible during flap motion to accommodate angle changes, and can provide sufficient rigidity when needed to resist air loads. This dynamic behavior allows the same structure to fulfill both adaptability and strength requirements throughout the operational cycle
Solution Approach 2:
The structural parameters of the transition piece, such as wall thickness and material properties, are optimized to achieve the desired balance between flexibility and rigidity. By carefully controlling these parameters, the structure can deform sufficiently for angle adaptation while maintaining adequate strength against aerodynamic loads
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
The solution effectively increases flap efficiency, reduces noise, and minimizes radar signatures by creating a continuous surface that can deform to match changing angles, improving aircraft aerodynamics and military applicability.
Implementation Method 1
a shear-compliant outer skin. The shear-compliant outer skin may comprise a biaxially woven metal mesh. The shear-compliant outer skin may also comprise an elastomer layer.
Implementation Method 2
The intersecting ribs can be pivotally connected to one another. a pantographic mechanism can be formed by the ribs.
Implementation Method 3
Gaps form when conventional flaps/control surfaces are in the extended state. These permit the air to flow through, which reduces the efficiency of the flap and generates noise.
Data Source
AI summary
A transition piece, which can be mounted in a recess, and which can form a continuous surface from a structural component of an airplane to a control surface, which is connected to the structural component in a pivotable manner is described. The transition piece can be mounted between an edge of the structural component and a lateral edge of the control surface such that the transition piece is fastened in a pivotable manner both to the edge of the structural component and to the lateral edge of the control surface. According to an example, the transition piece has a planar design and can be deformed within said plane, that is, the transition piece can be stretched or compressed within this plane.