Aircraft Access Cover Fastening for Wide Tolerance Assembly
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Solution Overview
Problem
Current access covers for aircraft holes require complex assembly, narrow tolerances, and separate parts, making them difficult to attach and detach efficiently, while also needing additional structural reinforcement to withstand aero loading.
Innovation Solution
A single-part access cover with a male fixing element and self-tightening nut configuration that allows for easy attachment and detachment using a simple screwdriver, featuring a locking mechanism that adjusts to varying structural thicknesses without requiring additional holes in the supporting structure, thus minimizing load transfer and weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a multi-part access cover with screws is used, then the cover can be securely attached to the aircraft structure, but the assembly becomes complex and time-consuming
Solution Approach 1:
The patent combines multiple separate components (inner cover, outer cover, and screw fastening system) into a single integrated access cover component. This single-piece design incorporates both the cover body and the fastening mechanism, eliminating the need for separate assembly of multiple parts while maintaining secure attachment to the aircraft structure.
Solution Approach 2:
The access cover is designed with functional segmentation within a unified structure, where different regions of the single component serve distinct purposes (cover function, fastening function, sealing function) without requiring physical separation into multiple parts. This resolves the contradiction by integrating functions rather than separating them.
2Reliability
If a multi-part access cover with screws is used, then the cover can be securely attached to the aircraft structure, but the assembly time increases
Solution Approach 1:
By merging the cover and fastening mechanisms into one integrated component, the installation process is simplified to a single attachment operation rather than multiple assembly steps, significantly reducing assembly time while maintaining secure attachment through the integrated fastening system.
Solution Approach 2:
The fastening mechanism is pre-integrated into the cover design during manufacturing, so that during installation, the cover is already prepared with built-in attachment capabilities. This preliminary integration eliminates the need for on-site assembly of separate fastening components, reducing assembly time.
3Reliability
If a narrow tolerance configuration is used for the access cover, then the cover can properly attach to the wing structure, but the manufacturing precision requirements increase
Solution Approach 1:
The patent employs tolerance compensation mechanisms and adjustable features in the single-piece design that allow the access cover to accommodate variations in structural thickness and positioning. This enables proper attachment with wider tolerances by dynamically adjusting fit parameters rather than requiring fixed, narrow tolerance specifications.
Solution Approach 2:
The access cover incorporates dynamic adjustment capabilities that allow it to adapt to varying structural conditions during installation. This dynamic adaptability enables proper attachment across a range of tolerances by adjusting the fit and positioning of the integrated fastening system to match the actual structural dimensions.
4Device complexity
If a single-part access cover is used, then the assembly complexity is reduced, but the ability to withstand aero loading may be compromised
Solution Approach 1:
The single-piece design merges the cover structure with an integrated fastening system specifically engineered to withstand aero loading. This consolidation allows for optimized load distribution paths through the unified structure, maintaining strength while simplifying assembly by eliminating joints and connections between separate parts that could become failure points.
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 solution enables quick and efficient attachment/detachment of the access cover with standard tools, accommodates wide structural tolerances, reduces assembly complexity, and avoids the need for structural reinforcement, maintaining aero performance and ease of maintenance.
Implementation Method 1
the friction between the male fixing element and the locking element causes the locking element to rotate with the male fixing element
Data Source
AI summary
An access cover for an aircraft hole that comprises a plurality of access cover holes, an inner surface, a plurality of first projections protruding from the inner surface, and a plurality of fixing elements configured to fix the access cover to a supporting structure of the aircraft hole. The fixing elements each comprise a male fixing element having an outer threaded surface, the male fixing element being configured to pass through a hole, and a locking element comprising a threaded hole and an extended portion, wherein the outer threaded surface of the male fixing element is configured to thread with the threaded hole of the locking element.