Wing Leading Edge Thermal Deformation Compensation
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Solution Overview
Problem
Conventional wing structures for aircraft experience disruptions in the boundary layer due to riveted connections and thermal deformations, leading to increased friction resistance and making it difficult to maintain a laminar flow, while also limiting the exchangeability of the wing leading edge.
Innovation Solution
A wing structure with a structural layer of fiber composite material and a protective steel foil layer, featuring a fixing-free section that allows for thermal deformation without constraining forces, and a fastening system using support elements and eccentric bushings to secure the wing leading edge to the wing box, ensuring a stable and exchangeable design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If riveted connections are used to attach the wing leading edge to the wing box, then structural strength and exchangeability are improved, but the boundary layer stability deteriorates due to disruptions in the flow surface
Solution Approach 1:
The harmful rivet heads are extracted from the flow surface by positioning all fastening elements internally within the wing box structure. The wing leading edge is attached to internal ribs and spars without any fastening protrusions on the external flow surface, eliminating boundary layer disruptions while maintaining structural strength through internal attachment mechanisms.
Solution Approach 2:
The fastening system is nested within the internal structure of the wing box. Support elements and fastening means are positioned inside the wing box, with the wing leading edge attached to internal ribs and spars. This nesting allows strong structural attachment while keeping the external flow surface clean and uninterrupted.
2Ease of manufacture
If the wing leading edge is made from aluminum material with riveted connections, then manufacturing ease and structural integrity are improved, but thermal deformation increases due to temperature differences between materials
Solution Approach 1:
The wing leading edge uses a localized steel foil erosion protection layer applied only to the external flow surface, while the internal structure remains aluminum. This local application of different materials provides erosion resistance where needed while minimizing thermal deformation, as the steel layer is thin and localized rather than throughout the entire structure.
Solution Approach 2:
The wing leading edge employs a composite structure combining aluminum internal framework with an external steel foil erosion protection layer. This composite design integrates the corrosion and erosion resistance of steel with the thermal properties and manufacturability of aluminum, reducing overall thermal deformation while maintaining durability.
3Reliability
If the wing leading edge structure is exposed to erosion, then the protective capability is reduced, but using thicker protective layers increases weight
Solution Approach 1:
A thin steel foil erosion protection layer is applied locally only to the external flow surface of the wing leading edge where erosion occurs during flight. This localized protective layer provides adequate erosion resistance without the weight penalty of thick protective layers throughout the entire wing structure.
Solution Approach 2:
The steel foil erosion protection layer is designed as a thin, replaceable protective covering that can be applied to the wing leading edge and replaced if damaged, rather than using heavy permanent protective structures. This approach provides reliable erosion protection while minimizing weight.
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 maintains a laminar boundary layer despite thermal deformations and allows for the secure and exchangeable wing leading edge, reducing friction resistance and enabling efficient fuel savings and extended aircraft range.
Implementation Method 1
proceeding from the joining section, a fixing-free section extends in the direction of a second side, which is situated opposite the first side, of the wing leading edge at least as far as the nose section, within which fixing-free section the wing leading edge is not fastened to the connecting elements
Implementation Method 2
the wing leading edge is, in at least one fastening section, fastened by means of in each case one support element which is articulatedly connected both to the wing leading edge and to the respective connecting element
Implementation Method 3
If an eccentric bushing is provided at one of the fastening points, said eccentric bushing is rotated until the elements can be connected in a force-free manner
Data Source
AI summary
The invention relates to a wing structure (1) for flying objects, comprising a wing leading edge (4) and a wing box (2), wherein the wing leading edge should be arranged on the wing box in particular in a detachable manner. For this purpose, the wing leading edge is connected to the wing box within a joining segment (9) and to rib extensions (11) of the wing box by means of fastening element (12) near the nose segment (15) such that a fastening-free segment (14) extends on the top side (16) of the wing leading edge in order to compensate thermal deformation during flight.