Aircraft Attachment Device With Oriented Bolt Axes
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Solution Overview
Problem
The complex manufacturing and assembly process of aerodynamic systems, such as aircraft wings, is hindered by the need for precise dimensioning and attachment of multiple components, which can be challenging due to tolerances and constraints.
Innovation Solution
An attachment device with multiple coupling units, each providing a bolted connection with a specific bolt axis orientation, allows for efficient tolerance compensation by enabling independent assembly and adjustment of components relative to the support structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If multiple components are attached with precise dimensioning and attachment, then the structural integrity and aerodynamic performance are improved, but the manufacturing and assembly process becomes complex and time-consuming
Solution Approach 1:
The attachment device is divided into multiple coupling units (first coupling unit, second coupling unit, etc.), each independently configured to couple the component to the support structure. This segmentation allows each coupling unit to be designed and assembled independently, reducing overall assembly complexity while maintaining precise attachment through multiple distributed connection points.
Solution Approach 2:
The bolt axes are configured with specific orientations (first bolt axis directed towards second bolt axis) to compensate for tolerances. By changing the geometric parameters of the bolted connections and allowing for tolerance compensation through the spatial arrangement of multiple coupling units, the system achieves precise attachment without requiring extremely tight manufacturing tolerances on individual components.
2Manufacturing precision
If multiple components are attached with precise dimensioning and attachment, then the structural integrity and aerodynamic performance are improved, but the assembly time and productivity are reduced
Solution Approach 1:
By segmenting the attachment system into multiple independent coupling units, each unit can be pre-assembled and tested separately, then quickly installed on the support structure. This modular approach reduces on-site assembly time while maintaining precise attachment through the distributed coupling units.
Solution Approach 2:
The coupling units are designed to be configured and prepared in advance with their specific bolt axis orientations and spacing. This preliminary configuration allows for faster on-site assembly, as the units are ready to be attached to the support structure without requiring complex adjustments during the assembly process.
3Ease of manufacture
If traditional bolted connections are used without specific axis orientation, then the assembly process is simpler, but tolerance accumulation and constraint forces increase
Solution Approach 1:
The bolt axes are specifically oriented (first bolt axis directed towards second bolt axis) to create a geometric configuration that naturally compensates for tolerances. This parameter change in the connection geometry allows the system to accommodate manufacturing variations without requiring complex adjustment procedures, maintaining both assembly simplicity and tolerance compensation capability.
Solution Approach 2:
The solution moves from considering only the local bolt connection to a three-dimensional spatial arrangement of multiple coupling units with specific axis orientations. By utilizing the spatial dimension and directing bolt axes towards each other, the system creates a self-compensating geometric configuration that handles tolerances across multiple dimensions simultaneously.
Data Source
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AI summary
The invention relates to an attachment device (1) for a support structure (111) of an aerodynamic system (110) of an aircraft (100). The attachment device (1) comprises a first coupling unit (10) configured to couple a component (30) to the support structure (111) via a first bolted connection (11) and a second coupling unit (20) spaced apart from the first coupling unit (10) and configured to couple the component (30) to the support structure (111) via a second bolted connection (21). The first bolted connection (11) defines a first bolt axis (12) and the second bolted connection (21) defines a second bolt axis (22). The first bolted connection (11) is configured such that the first bolt axis (12) is directed towards the second bolt axis (22). The invention further relates to a method for providing an attachment within an aerodynamic system (110).