Aircraft Seat Beam Assembly Using Deformed Recess Locking
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Solution Overview
Problem
The existing assembly methods for aircraft seats, which rely on screws and drilling, are cumbersome due to the need for multiple drilling references and increase the weight of the assembly, while also being inefficient in terms of assembly time and adaptable to varying seat configurations.
Innovation Solution
A method that deforms the beam passage zone to create a recess for the structural element, eliminating the need for screws and associated holes, allowing for easier configuration management and reduced weight by using a deformation tool to shape the beam for secure contact with the structural element.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If screws and drilling are used to assemble the beam and structural element, then the assembly is securely fastened, but the weight of the assembly increases and the number of drilling references must be planned in advance
Solution Approach 1:
The invention extracts and eliminates the screws and associated holes from the assembly system. Instead of using threaded fasteners, the patent employs a deformation mechanism where the beam passage zone is deformed to create an interference fit with the structural element, completely removing the need for separate fastening components and their associated weight.
Solution Approach 2:
The invention replaces the mechanical screw-fastening system with a deformation-based mechanical system. The beam passage zone is deformed using a specialized tool to create a recess that mechanically interlocks with the structural element, substituting the screw-thread mechanism with a deformation-induced interference fit.
2Strength
If screws and multiple drilling references are used, then the assembly is secure, but the assembly time increases due to numerous screwing operations
Solution Approach 1:
The invention merges the positioning and fastening functions into a single operation. The deformation tool simultaneously creates the recess and secures the structural element to the beam in one continuous action, eliminating the separate steps of drilling, countersinking, and screwing that characterize traditional assembly methods.
Solution Approach 2:
The invention performs preliminary deformation of the beam passage zone to create the recess before final assembly. This preliminary action prepares the beam to receive the structural element, ensuring proper positioning and securement in a single subsequent operation rather than requiring multiple sequential fastening steps.
3Adaptability or versatility
If multiple drilling references are planned in advance for different seat configurations, then various configurations can be accommodated, but the device complexity and manufacturing planning increase
Solution Approach 1:
The invention introduces dynamics to the assembly system by enabling the beam passage zone to be deformed into different configurations. Rather than having fixed drilling references for each seat type, the deformation tool can create different recess patterns on-demand, allowing the same beam to adapt to various seat configurations through controlled deformation.
Solution Approach 2:
The invention changes the physical state and geometry of the beam passage zone through deformation. By applying controlled force with the deformation tool, the beam material is permanently reshaped to create different recess configurations, allowing parameter changes in the beam's geometry to accommodate different seat types without requiring different drilling templates.
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 simplifies the assembly process, reduces weight, and saves time by avoiding screwing operations, while enabling flexibility in managing diverse seat configurations through deformation of the beam's internal face to match the structural element's external face.
Implementation Method 1
a method of assembly between a beam (13) and a structural element (11, 12) of an aircraft seat, comprising a step of deforming the beam passage zone (15), so that at least a portion of an internal face of said beam passage zone comes to bear against an external face of the beam along a contact surface
Data Source
Figure 1~2a
Figure 2b~3
Figure 4a~4b
AI summary
The present invention essentially relates to a method for assembling a beam (13) and a structural element (11,12) of an aircraft seat, characterised in that it comprises: - a step of producing at least one recess (19) in an inner face of a beam passage area (15) of the structural element (11, 12), - a step of inserting the beam (13) into the beam passage area (15), and - a step of deforming the beam (13) such that a deformed portion (27) of the beam (13) penetrates into the recess (19) of the beam passage area (15).