Aircraft Interior Cladding Surface Change Element
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Solution Overview
Problem
Conventional aircraft interior claddings require complex and costly processes for repair or exchange, involving the dismantling of adjacent elements and lengthy material testing, which increases downtime and costs due to the nested construction and need for EASA certification.
Innovation Solution
An aircraft interior cladding system with a detachable, dimensionally stable surface change element comprising a carrier element with successive fiber fabric layers and a decorative element, allowing for quick exchange and repair by producing identical elements prior to actual installation, enabling pre-testing and reducing the need for extensive dismantling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of repair
If conventional aircraft interior cladding is exchanged or repaired, then the damaged cladding is replaced, but the process requires extensive dismantling of adjacent elements and lengthy material testing, increasing downtime and costs
Solution Approach 1:
The cladding system is divided into modular panels that can be independently removed and replaced. Each panel consists of a structural element with a detachably connected surface element, allowing the surface layer to be exchanged without removing the entire panel or adjacent components, significantly reducing repair time and downtime.
Solution Approach 2:
Replacement surface elements are pre-manufactured and pre-tested for compliance with aeronautical specifications before being installed. This preliminary preparation ensures that when damage occurs, the replacement elements are already certified and ready for immediate installation, eliminating the need for lengthy on-site material testing and approval processes.
2Ease of repair
If conventional aircraft interior cladding is exchanged or repaired, then the damaged cladding is replaced, but the nested construction requires dismantling of adjacent elements, increasing costs and complexity
Solution Approach 1:
The cladding system is divided into modular panels that can be independently removed and replaced. Each panel consists of a structural element with a detachably connected surface element, allowing the surface layer to be exchanged without removing the entire panel or adjacent components, significantly reducing repair time and downtime.
Solution Approach 2:
The connection between structural elements and surface elements is designed to be dynamically changeable - permanently fixed during installation but easily detachable during maintenance. This dynamic connection system allows for simple replacement of surface elements while maintaining structural integrity during operation.
3Reliability
If conventional aircraft interior cladding is exchanged or repaired, then the damaged cladding is replaced, but material testing and EASA certification are required, increasing time and costs
Solution Approach 1:
Replacement surface elements are pre-manufactured and pre-tested for compliance with aeronautical specifications before being installed. This preliminary preparation ensures that when damage occurs, the replacement elements are already certified and ready for immediate installation, eliminating the need for lengthy on-site material testing and approval processes.
Solution Approach 2:
The invention changes the certification parameter from individual site-specific installations to standardized pre-certified components. By establishing that surface elements meet specified material properties and fire safety standards during manufacturing, the certification process shifts from repeated field testing to one-time factory certification, dramatically reducing approval time.
Data Source
AI summary
In summary, the present application relates to an aircraft interior paneling (10) comprising: —a planar replaceable surface element (40); —a structural element (20); —at least one connection element (30); wherein the replaceable surface element (40) is detachably fastened to the structural element (20) by means of the at least one connection element (30), and wherein the replaceable surface element (40) comprises: —a support element (42), wherein, in the thickness direction of the support element (42), the support element (42) comprises a plurality of successive layers which comprise woven fabrics; —a decorative element (50) which is attached to a decorative connection surface (52) of the support element (42), wherein the support element (42) is dimensionally stable; and a replaceable surface element (40) for an aircraft interior paneling (10); the use of a replaceable surface element (40) for an aircraft interior paneling (10); a method for producing a replaceable surface element (40) for an aircraft interior paneling (10); and a method for updating an existing aircraft interior paneling (100).