Aircraft Fuselage Lining Holding Device with Sacrificial Tube
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Solution Overview
Problem
Existing solutions for securing interior lining parts in aircraft fuselages are heavy, difficult to implement, and may not ensure that the primary structure is protected from loads and rapid decompression, as they rely on complex frame elements and rods that are hard to design for failure without damaging the lining parts.
Innovation Solution
A holding device with a joint anchored to the fuselage primary structure, a connecting tube, and an arrester cable or lanyard that allows the connecting tube to fail before the supporting device and lining part, ensuring moment-free attachment and preventing uncontrolled movement during pressure drops, while reducing weight and allowing for multiple lightweight attachment points.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a supporting framework with frame elements and rods is used to secure interior lining parts, then the primary structure is protected from loads and moments, but the system becomes heavy and complex
Solution Approach 1:
The patent removes the complex frame elements and rods from the supporting framework, retaining only the essential mounting points directly attached to the primary structure. This extraction of unnecessary components significantly reduces weight while maintaining the core function of protecting the primary structure through properly positioned mounting points.
Solution Approach 2:
The supporting framework is segmented into discrete mounting points distributed throughout the fuselage interior, replacing the continuous complex frame structure. Each mounting point is independently positioned to provide optimal protection while minimizing weight, allowing the system to achieve strength through strategic placement rather than comprehensive coverage.
2Strength
If frame elements and rods are used to secure interior lining parts, then attachment strength is improved, but the device complexity increases
Solution Approach 1:
The patent extracts and eliminates the complex frame elements and rods, keeping only the essential mounting points that provide sufficient attachment strength. This simplification removes unnecessary structural components while retaining the core attachment function through strategically positioned mounting points.
Solution Approach 2:
Instead of building up strength through multiple interconnected frame elements and rods, the patent inverts the approach by using minimal discrete mounting points that leverage the primary structure's inherent strength. The solution achieves attachment strength through subtraction and strategic placement rather than addition and complex interconnection.
3Strength
If rods are designed to fail before frames and lining parts, then primary structure protection is ensured, but it is difficult to guarantee controlled failure sequence
Solution Approach 1:
The patent removes the rods entirely, eliminating the complex failure sequence design problem. Without rods to coordinate, the system achieves primary structure protection through mounting points that are inherently designed to fail in a controlled manner, simplifying the reliability of the failure sequence.
Solution Approach 2:
The mounting points are designed as sacrificial elements that are intended to fail under excessive load, protecting the primary structure. These mounting points are simpler and more reliable than rods because they are designed from the outset to fail in a predictable manner rather than requiring complex coordination with frames and other components.
4Strength
If multiple attachment points are used to secure interior lining parts, then load distribution is improved, but weight increases with traditional frame structures
Solution Approach 1:
The supporting framework is segmented into multiple discrete mounting points distributed throughout the fuselage interior. This segmentation allows load to be distributed across many lightweight points rather than concentrated in heavy frame structures, achieving superior load distribution with minimal weight by leveraging the primary structure's inherent load-bearing capacity.
Data Source
AI summary
A holding device for in particular panel-shaped interior lining parts of a fuselage, has a configuration that is easy and simple to mount, each holding device includes a supporting device, which is used to anchor the holding device on a primary structure of the fuselage and comprises a joint; a connecting tube, which extends out of the supporting device and one end of which is attached to the joint; a mounting for an interior lining part, to which mounting the other, opposite end of the connecting tube to the one end is attached; and a lanyard, which is fastened to the supporting device is and the mounting and extends through the connecting tube and the length of which is greater than the length of the connecting tube.