Aircraft Interior Coupling Assembly for Tool-Free Tolerance Mounting
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Solution Overview
Problem
The assembly of aircraft cabin interiors requires significant manual effort and lacks automation, particularly in mounting interior components to the primary structure.
Innovation Solution
A coupling kit-of-parts comprising a locking member, a mounting member with first and second member parts forming a locking channel, and an elastic member to facilitate automated and tool-free mounting of interior substructures to a primary aircraft structure, allowing for tolerance compensation and secure attachment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Extent of automation
If manual assembly methods are used for mounting interior components to aircraft primary structure, then flexibility and adaptability are maintained, but automation extent and productivity are reduced
Solution Approach 1:
The mounting member is divided into first and second member parts that can move relative to each other, allowing the system to transition between locked and unlocked states. This segmentation enables automated operation while maintaining manageable complexity through modular design
Solution Approach 2:
The elastic member automatically urges the first and second member parts into engagement with the locking member without requiring external actuation. The system self-regulates the mounting process through elastic forces, reducing the need for complex control mechanisms
2Productivity
If traditional fastening systems are used, then manufacturing precision requirements are reduced, but productivity and automation capability are limited
Solution Approach 1:
The first and second member parts are designed to move dynamically relative to each other during the mounting process. This dynamic capability allows the system to adapt to manufacturing tolerances while maintaining high mounting speed through automated insertion and locking actions
Solution Approach 2:
The system changes the physical state of the member parts from movable to fixed when locked into place. This parameter change enables the mounting process to accommodate tolerance variations while achieving rapid, automated fixation
3Reliability
If simple locking mechanisms are used, then device complexity is reduced, but reliability under vibration and mechanical resistance are compromised
Solution Approach 1:
The locking member features a spherical head that engages with corresponding curved surfaces in the locking channel. This spherical geometry provides inherent mechanical resistance to vibration and rotational forces while maintaining a relatively simple overall structure
Solution Approach 2:
The locking function is merged with the mounting operation itself - the same first and second member parts that form the mounting structure also create the locking channel and provide the locking action. This integration improves reliability by eliminating separate locking components while keeping device complexity manageable
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
Enables automated, tool-free, and vibration-resistant mounting of interior components to aircraft structures, compensating for manufacturing tolerances and ensuring reliable installation and removal.
Implementation Method 1
a kit-of-parts further comprises an elastic member that is arranged to urge the first and second member parts radially inward along the radial direction such that, when the locking member is removed from the locking channel, the first and second member parts are pushed radially inward by the elastic member
Data Source
AI summary
A coupling kit-of-parts is provided for mounting an interior substructure to a primary structure of an aircraft. The kit includes a locking member and a mounting member. When the locking member is inserted into the mounting member, a first member part and a second member part are pushed radially outward to engage the primary structure in a form-fitting manner. When the locking member is removed, the first and second member parts are urged radially inward thereby disengaging from the primary structure.