Composite Former with Opening for Stringer Attachment
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Solution Overview
Problem
The existing composite aircraft structures relying on clips for attaching stringers and formers are costly due to the large number of different clip types required, leading to inefficient production processes.
Innovation Solution
The use of fibre composite material formers that form an opening with the skin portion, allowing the stringer to extend through it, eliminating the need for clips and reducing production costs by enabling direct attachment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If clips are used to attach formers to the skin portion, then the former can be securely attached, but the number of different clip types increases significantly (over 200 types), leading to high production costs and complex manufacturing processes
Solution Approach 1:
The invention extracts and eliminates the clips from the attachment system. Instead of using clips to connect the former to the skin portion, the former is directly attached to the skin portion through integrated attachment means (such as attachment lugs or direct bonding), thereby removing the source of complexity while maintaining secure attachment.
Solution Approach 2:
The invention merges the former with the skin portion by integrating the attachment function directly into the former structure. The former includes attachment means that are part of its structure, eliminating the need for separate clip components and reducing the overall system complexity.
2Adaptability or versatility
If multiple types of clips are used for different geometries, then various attachment configurations are achieved, but production costs increase due to the need for over 200 different production means
Solution Approach 1:
The invention applies universality by designing the former with integrated attachment means that can accommodate different attachment configurations without requiring different clip types. The same former design with attachment lugs or bonding surfaces can be used across various applications, reducing the number of production means required.
Solution Approach 2:
The invention changes the attachment approach from mechanical clips to alternative methods such as direct bonding or integrated attachment lugs. This parameter change in the attachment mechanism eliminates the need for multiple clip geometries while maintaining the ability to achieve various attachment configurations.
3Ease of operation
If clips are used to connect formers and stringers, then the structure is assembled, but the manufacturing process becomes inefficient and costly
Solution Approach 1:
The invention extracts the clips from the assembly process and replaces them with direct attachment methods. The former is attached directly to the skin portion and stringers pass through openings in the former, eliminating the need for clip installation steps and improving manufacturing efficiency.
Solution Approach 2:
The invention applies preliminary action by pre-integrating attachment means into the former during its manufacturing process. The attachment lugs or bonding surfaces are formed as part of the former fabrication, allowing for more efficient final assembly without requiring separate clip installation operations.
Data Source
AI summary
The present invention provides a composite for an aircraft or spacecraft, comprising: a skin portion; a stringer which is attached to the skin portion; and a former made from fibre composite material, which is attached to the skin portion and forms an opening therewith, through which the stringer extends, substantially transverse to the former.