Aircraft Framework Assembly With Adjustable Plug-and-Turn Coupling
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Solution Overview
Problem
The manufacturing of complex structural frameworks, such as aircraft fuselages, is time-consuming and prone to internal stress due to non-compensated tolerances, requiring numerous rivets or welds and additional materials for compensation.
Innovation Solution
A pole-shaped aircraft framework assembly with plug-and-turn connectors and a coupling component featuring ridged and plain sections, allowing for adjustable length and easy assembly by plugging and rotating the connectors for secure fixation, reducing the need for multiple components and minimizing internal stress.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If traditional manufacturing methods using rivets or screws are employed to connect structural components, then the framework can be assembled with fixed-length components, but the manufacturing process becomes time-consuming and requires numerous fasteners at each connection point
Solution Approach 1:
The framework is divided into modular structural components with standardized connection interfaces. Each component can be independently manufactured and assembled, allowing parallel production and reducing overall assembly time while maintaining structural integrity through repeated modular units.
Solution Approach 2:
A universal connector design is implemented that can accommodate various structural components with different orientations and positions. This single multi-functional connector replaces multiple specialized fasteners, reducing the total number of connection elements needed while maintaining assembly speed.
2Device complexity
If welding or gluing is used to connect structural components, then the number of connection elements is reduced, but the manufacturing process remains time-consuming and may create internal stress
Solution Approach 1:
Traditional mechanical fastening methods (rivets, screws, welds) are replaced with a friction-based mechanical insertion system. The connection is achieved through friction between the connector and structural component surfaces, eliminating the need for thermal or chemical joining processes while maintaining connection strength and reducing manufacturing time.
3Manufacturing precision
If shims or additional materials are used to compensate for tolerances and unintended distances, then structural components can be connected despite manufacturing variations, but the assembly process becomes more complex and time-consuming
Solution Approach 1:
The connector design incorporates adjustable and adaptable features that allow dynamic adjustment during assembly to accommodate manufacturing tolerances and unintended distances. The friction-based connection system can compensate for variations through elastic deformation and friction adjustment, eliminating the need for rigid shims or additional compensating materials.
4Strength
If multiple rivets or screws are used at each connection point, then structural integrity is maintained, but internal stress increases due to non-compensated tolerances
Solution Approach 1:
The friction-based connector acts as an intermediary element that distributes and compensates for tolerance variations between structural components. This intermediary absorbs dimensional variations through elastic deformation and friction adjustment, maintaining structural integrity while preventing stress concentration that would occur with rigid mechanical fasteners.
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 fast, cost-effective, and stress-free assembly of aircraft structural frameworks by allowing adjustable length and secure engagement of components, thereby reducing manufacturing time and costs while avoiding internal stresses.
Implementation Method 1
The circumferential outer surface of the first rod includes alternately on a circumferential path in a cross-sectional plane of the first rod at least one ridged section and at least one plain section... The circumferential inner surface of the tubular part includes alternately on a circumferential path in a cross-sectional plane of the tubular part at least one ridged section and at least one plain section
Implementation Method 2
a first plug-and-turn connector forming a first end of the pole-shaped aircraft framework assembly, and a second plug-and-turn connector forming a second end of the pole-shaped aircraft framework assembly... configured for detachable coupling with the first rod
Data Source
AI summary
A pole-shaped aircraft framework assembly including a first plug-and-turn connector forming a first end, a second plug-and-turn connector forming a second end, the second end opposite the first end, a first rod extending from the first plug-and-turn connector towards the second plug-and-turn connector, and a coupling component coupled to the second plug-and-turn connector for detachable coupling with the first rod. The first rod has a circumferential outer surface including alternately on a circumferential path in a cross-sectional plane of the first rod a ridged section and a plain section. The coupling component includes a tubular part having a circumferential inner surface including alternately on a circumferential path in a cross-sectional plane of the tubular part at least one ridged section and at least one plain section. One of the first rod and the coupling component is rotatable relative to the other one, engaging respective ridges of the first rod and the coupling component.