Aircraft Insert Locking Mechanism for Flush, Fast Assembly
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Solution Overview
Problem
Aircraft components often require numerous inserts that are time-consuming and labor-intensive to assemble, with existing methods lacking efficiency in securing these inserts consistently and quickly.
Innovation Solution
The development of a self-adjusting insert system featuring a central axis, locking mechanism, and compression mechanism that aligns and secures itself within a recess of an aircraft component, allowing for rapid and consistent positioning without manual adjustment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional insert assembly methods are used, then inserts can be securely attached to aircraft components, but assembly time and labor costs increase significantly
Solution Approach 1:
The insert is pre-loaded into the tool with the compression mechanism already in place. The tool is positioned over the recess before the insert is fully installed, allowing the compression mechanism to be compressed and the locking mechanism to engage with the recess walls in advance of final insertion. This preliminary positioning and pre-compression reduces the time required during final assembly while ensuring secure attachment.
Solution Approach 2:
The insert incorporates a self-adjusting locking mechanism that automatically engages with the recess walls when compressed. The locking mechanism with tabs or protrusions that fit into corresponding features on the recess walls provides self-alignment and self-securing functionality. This self-service capability eliminates the need for manual adjustment or additional fastening steps, reducing assembly time while maintaining reliable attachment.
2Manufacturing precision
If manual positioning methods are used, then inserts can be precisely positioned relative to aircraft components, but labor intensity and assembly complexity increase
Solution Approach 1:
The insert features a self-aligning locking mechanism with tabs or protrusions that automatically position themselves relative to the recess walls during compression. The geometry of the locking mechanism and recess are designed to guide the insert into correct alignment as it is inserted, eliminating the need for manual positioning adjustments. This self-positioning capability maintains manufacturing precision while dramatically improving ease of operation.
Solution Approach 2:
The compression mechanism applies force uniformly along the central axis of the insert, creating an equipotential compression state that ensures even distribution of loading across the locking mechanism. This uniform compression facilitates consistent positioning and engagement of the locking features with the recess, achieving precise alignment without requiring manual intervention or complex positioning procedures.
3Manufacturing precision
If compression force is applied to secure the insert, then the insert integrates flush with the aircraft component, but excessive force may damage the component
Solution Approach 1:
The compression mechanism is designed with controlled compliance, allowing it to deform progressively under applied load. The spring elements or compliant features in the compression mechanism absorb excess force through elastic deformation, preventing transmission of damaging peak loads to the aircraft component. This dynamic response enables achievement of flush integration while protecting component integrity through controlled force distribution.
Solution Approach 2:
The compression mechanism incorporates cushioning elements such as spring features or compliant layers that are positioned between the insert and the aircraft component before compression is applied. These cushioning elements prevent direct transmission of high impact forces to the component during the compression process, while still allowing the insert to be pressed flush against the component surface. The cushioning action protects component integrity while achieving the desired flush integration.
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 enables rapid and consistent assembly of inserts, reducing assembly time and labor costs while ensuring secure, flush integration with aircraft components, enhancing both strength and aesthetics.
Implementation Method 1
a compression mechanism coupled to the second portion
Data Source
AI summary
The present disclosure provides an insert that includes a locking mechanism that may either be formed integrally to the component or attached separately to the insert body. The top of the locking mechanism is offset from the first surface by an offset distance to enable the insert to be coupled to a recess of a component such as an aircraft component. An aperture formed in a top surface of the first portion is configured to allow additional elements to be coupled to the aircraft component. The coupling of the insert to the aircraft component is further promoted by a compression mechanism that forces the locking mechanism to couple to an overhang portion of the top layer after the force applied to the insert once it is positioned in the recess is removed, such that the top surface of the insert is co-planar with an outermost surface of the aircraft component.