Aircraft Wing Fastening System With Deformable Shaft
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Solution Overview
Problem
The joining of structural members in aircraft wing construction is time-consuming and adds significant weight due to the use of traditional fasteners, and existing solutions do not effectively address the need for a lightweight, efficient method that allows for easy access and reconfiguration of the wing box without compromising structural integrity.
Innovation Solution
A mechanical fastening system that includes a first and second structural member with partial bores and protrusions, aligned to form a through-bore, and a shaft with engagement members that utilize mechanical deformation for secure clamping, allowing for easy assembly and disassembly, and potentially incorporating a bolt member with a through-bore for reduced weight and routing of wires/hoses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional fasteners are used to join structural members, then structural integrity is maintained, but the weight of the aircraft increases significantly and assembly time increases
Solution Approach 1:
The fastening system is divided into separate functional components: a first engagement member with first protrusions, a second engagement member with second protrusions, and a shaft with through-bore. This segmentation allows each component to be optimized independently for its specific function while reducing overall weight compared to traditional monolithic fasteners.
Solution Approach 2:
The invention extracts the essential fastening function from traditional heavy fasteners by using protrusions that engage with corresponding recesses in the structural members. The shaft with through-bore provides a lightweight alternative to traditional threaded fasteners, removing unnecessary material while maintaining structural integrity.
2Strength
If traditional fasteners are used to join structural members, then structural integrity is maintained, but the assembly time increases significantly
Solution Approach 1:
The engagement members and shaft are designed with pre-formed protrusions and corresponding recesses that align automatically during assembly. This preliminary geometric preparation eliminates the need for time-consuming alignment procedures and traditional fastening operations, allowing for rapid assembly while maintaining structural integrity.
Solution Approach 2:
The fastening system features self-aligning protrusions and recesses that automatically position components correctly during assembly. The shaft with through-bore requires no additional threading or fastening operations, allowing the structure to essentially assemble itself through the inherent geometry of the engagement members.
3Ease of operation
If a two-piece rib design is used to allow access to wing box, then maintenance access is improved, but the complexity of aligning and joining rib portions increases
Solution Approach 1:
The engagement members feature asymmetric protrusion patterns that provide self-alignment during assembly. The first protrusions and second protrusions are positioned at specific locations that guide the rib portions into correct alignment, eliminating complex alignment procedures while maintaining the ability to access the wing box through the two-piece design.
4Strength
If traditional fastening methods are used, then structural connection is achieved, but the weight of fasteners adds significant mass to the aircraft
Solution Approach 1:
The fastening system applies local quality by concentrating the fastening function into specific protrusion points rather than requiring extensive fastening material throughout the connection area. The shaft with through-bore provides localized structural connection only where needed, reducing overall fastener weight while maintaining adequate structural connection strength.
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
The system enables efficient joining and separation of structural members, providing a lightweight, self-centering, and tension-resistant connection that reduces the overall weight of the aircraft while allowing for easy access and maintenance of the wing box.
Implementation Method 1
said first end portion of said shaft comprises a mechanical deformation in abutting engagement with said first engagement member; and/or said second end portion of said shaft comprises a mechanical deformation in abutting engagement with said second engagement member
Data Source
Figure 1
Figure 2
Figure 3A
AI summary
A structural assembly including a first structural member defining a first partial bore and including a first protrusion and a second protrusion, a second structural member defining a second partial bore and including a first protrusion and a second protrusion, wherein the second partial bore is aligned with the first partial bore to define a through-bore, a shaft extending through the through-bore, wherein the shaft includes a first end portion and a second end portion, a first engagement member proximate the first end portion, wherein the first engagement member engages both the first protrusion of the first structural member and the first protrusion of the second structural member, and a second engagement member proximate the second end portion, wherein the second engagement member engages both the second protrusion of the first structural member and the second protrusion of the second structural member.