Modular Wing Edge Tension Joint for Fast Assembly Access
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Solution Overview
Problem
The existing wing assembly construction methods are time-consuming due to the need for precise tolerances and the use of shims to compensate for deviations, which complicates manufacturing and maintenance, especially when accessing internal components.
Innovation Solution
A modular edge system with a tension joint, comprising a pivotally mounted modular edge and a main structure, where a tension bolt forms a secure alignment and attachment, allowing for standardized manufacturing and easier assembly and maintenance by accommodating tolerance gaps and providing access to internal components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If traditional fixed leading and trailing edge structures are used with precise tolerance control, then aerodynamic performance is maintained, but manufacturing time increases due to the need for shims and fettling to compensate for tolerance gaps
Solution Approach 1:
The wing edge is divided into modular components (leading edge, trailing edge, wing box) that can be manufactured separately with standard tolerances and then assembled together. The modular edge assembly includes the edge structure, ribs, and fasteners as integrated sub-assemblies, enabling parallel manufacturing and reducing overall production time while maintaining aerodynamic precision through the modular interface design.
Solution Approach 2:
The invention changes the approach from controlling dimensional parameters of individual components to controlling the relative position parameters through the modular interface. The first and second contact faces provide a standardized interface that absorbs tolerance variations, allowing components to be manufactured with relaxed tolerances while maintaining the required aerodynamic shape through the assembled configuration.
2Manufacturing precision
If shims and fettling techniques are used to compensate for tolerance gaps, then aerodynamic shape is maintained, but assembly complexity and time increase
Solution Approach 1:
The modular edge components are pre-assembled and pre-aligned as complete sub-assemblies before final installation on the wing box. The contact faces and fastening interfaces are prepared in advance during modular assembly, so that during final wing assembly, the components simply need to be positioned and secured, eliminating the need for on-site shimming and fettling operations.
Solution Approach 2:
The first and second contact faces act as intermediary elements between the modular edge and the wing box structure. These contact faces provide a standardized interface that accommodates tolerance gaps without requiring additional compensating elements like shims. The tension bolt system works through these contact faces to secure the modular edge, simplifying the assembly process.
3Ease of repair
If the wing is partially disassembled to access internal components, then maintenance can be performed, but reassembly time increases due to the need to ensure design shape conformity
Solution Approach 1:
The modular edge design allows the leading edge or trailing edge to be separated as a distinct module from the wing box structure. This segmentation enables maintenance personnel to remove and access internal components by simply detaching the modular edge assembly, without needing to disassemble the entire wing structure. The standardized interface with contact faces and fasteners enables quick removal and reattachment.
Solution Approach 2:
The modular edge assembly is designed to be self-contained with all necessary components (edge structure, ribs, fasteners) integrated into the module. During maintenance, the entire modular edge can be removed as one unit, allowing access to internal components. The module can then be reinstalled by simply reversing the removal process, as the self-contained design ensures proper alignment and shape conformity without requiring complex reassembly procedures.
4Strength
If multiple fasteners are used to secure the modular edge, then structural integrity is maintained, but the number of components and assembly steps increases
Solution Approach 1:
The function of multiple fasteners is merged into a single tension bolt system. The tension bolt is designed to engage with both the first contact face on the wing box and the second contact face on the modular edge, providing both positioning and securing functions in one component. This merging reduces the number of fasteners from multiple separate fastening elements to a single multi-functional tension bolt, simplifying the assembly while maintaining structural integrity.
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 solution enhances manufacturing efficiency, reduces the number of fasteners required, and simplifies maintenance by allowing quick rotation of the modular edge for improved access to internal wing components, while maintaining aerodynamic performance.
Implementation Method 1
tension in a tension bolt received in the first and second recesses acts to press the first and second contact faces together, thereby forming a tension joint that resists pivoting of the modular edge relative to the main structure
Implementation Method 2
the modular edge is pivotally mounted on the main structure by one or more fasteners, each fastener constraining the modular edge relative to the main structure in all degrees of freedom except rotation about a longitudinal axis of the fastener
Data Source
Figure 1~2
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Figure 4
AI summary
A wing assembly (2) is disclosed. The wing assembly (2) comprises a main structure (103) comprising a first contact face (131) and a first recess (123) arranged to receive a portion of a tension bolt (125); and a modular edge (101) comprising a second contact face (129) and a second recess (113) arranged to receive a portion of the tension bolt (125). The modular edge (101) is pivotally mounted on the main structure (103) for rotation between an installation position and an operational position in which the modular edge (101) is aligned with the main structure (103) to form at least part of an edge of the wing assembly (2). The wing assembly (2) is arranged such that, when the modular edge (101) is in the operational position, tension in a tension bolt (125) received in the first and second recesses (123, 113) acts to press the first and second contact faces (131, 129) together, thereby forming a tension joint that resists pivoting of the modular edge (101) relative to the main structure (103).