Composite Insert Assembly Using Snap-In Alignment in Panel Bores
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Solution Overview
Problem
Existing methods for attaching composite inserts to components, such as aircraft floor panels, are difficult and can damage the panels, especially when using two-part inserts that require hammering or stationary pressing.
Innovation Solution
A method involving a sleeve element and a plug-in element, where the sleeve is arranged in a bore, connected to the plug-in element, and a snap-in device is used to align and secure them with adhesive applied beforehand, preventing damage and ensuring secure attachment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If two-part inserts are joined using a hammer or stationary press, then the insert can be securely attached to the component, but the composite core panel can be easily damaged and the installation becomes difficult or impossible
Solution Approach 1:
The patent replaces the traditional mechanical joining method (hammer or stationary press) with a snap-in device that uses elastic deformation and geometric interlocking. The snap-in device features an elastic portion that deflects during insertion and then locks into place, providing secure attachment without requiring high-impact mechanical forces that could damage the composite panel
Solution Approach 2:
The patent changes the physical state and properties of the joining mechanism by using an elastic material for the snap-in device. The elastic portion can reversibly deform under load, allowing for controlled insertion and secure locking. This parameter change from rigid to elastic behavior enables damage-free attachment while maintaining strong bonding
2Strength
If two-part inserts are joined using a hammer or stationary press, then the insert can be securely attached, but the installation process becomes difficult or not possible in aircraft settings
Solution Approach 1:
The patent replaces the complex stationary press or hammering equipment with a simple snap-in device that can be manually operated. The elastic portion naturally deflects during insertion and locks into place through geometric interlocking, eliminating the need for heavy machinery and making the installation process suitable for aircraft maintenance environments
Solution Approach 2:
The snap-in device is designed to be self-aligning and self-locking. The elastic portion automatically deflects during insertion and engages with the corresponding feature in the composite panel, providing secure attachment without requiring external equipment or complex alignment procedures
3Reliability
If adhesive is applied into the bore and/or onto the sleeve element prior to placement, then secure attachment and protection against fluids/contaminants is achieved, but additional assembly steps are required
Solution Approach 1:
The patent applies adhesive to the bore and/or sleeve element before assembly, allowing the adhesive to begin curing and forming a strong bonding interface. This preliminary action ensures reliable attachment and creates a protective seal against fluids and contaminants before the final locking operation occurs
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 method allows for efficient, safe, and quick attachment of composite elements to components without damaging them, enabling reproducible and identical arrangements, and provides a secure, preloaded connection with an adhesive layer for protection against fluids and contaminants.
Implementation Method 1
prior to locating the socket member an adhesive is applied into the bore and/or onto the socket member
Data Source
Figure 1(A)~1(C2)
Figure 2
Figure 3
AI summary
The present invention relates to a method for arranging at least one composite element (2) on a component (18), wherein the at least one composite element (2) comprises at least one sleeve element (4) and at least one plug-in element (6). The method comprises the following steps: arranging the sleeve element (4) in a bore (20) of the component (18); connecting the sleeve element (4) to the plug-in element (6) so that the at least one composite element (2) is formed; inserting a snap-in device (24, 25) into the at least one composite element (2), wherein the snap-in device (24, 25) aligns and/or joins the sleeve element (4) and the plug-in element (6) relative to each other.The invention also includes the use of a snap-in device (24, 25) and at least one composite element (2) for arranging the at least one composite element (2) on a component (18), wherein the at least one composite element (2) comprises a sleeve element (4) and a plug-in element (6) and the snap-in device (24, 25) aligns and/or joins the sleeve element (4) and the plug-in element (6) to each other.