Aircraft Monument Frame Assembly With Non-Structural Panels
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Solution Overview
Problem
Traditional monument enclosures in aircraft use structural composite panels that are inefficient, require large, expensive, and heavy machined frames, and are costly due to the use of thick aluminum honeycomb and aluminum skinned panels.
Innovation Solution
A monument assembly with a load-bearing frame formed by connecting support members together, using common extrusions and floor fittings to anchor the assembly to the aircraft floor, shifting the load path from panels to the frame, allowing for efficient fabrication with less expensive materials and customization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If structural composite panels are used as main strengthening components, then the enclosure can support loads during aircraft operation, but the panels become extremely heavy and expensive
Solution Approach 1:
The patent inverts the traditional design approach by making the frame the primary load-bearing component rather than the panels. The frame is designed to react all loads imposed by the enclosure's contents, while the panels serve only as non-structural coverings. This inversion resolves the contradiction by eliminating the need for heavy structural panels while maintaining load-bearing capacity through the frame structure.
Solution Approach 2:
The patent extracts the load-bearing function from the panels and assigns it exclusively to the frame. By separating the structural and non-structural functions, the panels can be made from lightweight materials without compromising strength, while the frame independently handles all loading requirements.
2Strength
If large, machined frames are used to support structural panels, then the panels can be secured, but the frames become extremely expensive and heavy
Solution Approach 1:
The patent inverts the traditional hierarchy by making the frame the load-bearing element rather than a support structure for panels. The frame is designed to directly react enclosure loads and is connected to the aircraft floor, eliminating the need for heavy machined frames to support structural panels.
Solution Approach 2:
The patent changes the functional parameters of the frame from being a panel support structure to being the primary load-bearing component. This parameter change allows the frame to be optimized for strength and weight efficiency while the panels are optimized for lightweight construction.
3Strength
If thick aluminum honeycomb and aluminum skinned panels are used, then the enclosure has sufficient structural strength, but the material cost and weight increase significantly
Solution Approach 1:
The patent extracts the structural strength requirement from the panels and assigns it to the frame. This allows the panels to be constructed from lightweight, non-structural materials with minimal thickness, dramatically reducing material quantity while maintaining overall enclosure strength through the frame.
Solution Approach 2:
The patent replaces expensive structural aluminum panels with cheaper, non-structural panel materials that do not need to bear loads. The frame assumes all structural responsibilities, allowing panel materials to be selected based on cost and weight considerations rather than structural requirements.
Data Source
AI summary
A monument assembly for a vehicle and method for attaching a monument assembly to an aircraft. The monument assembly is capable of being a heavily loaded interior monument enclosure for an aircraft that includes a load bearing structural frame to be attached to a floor of the aircraft. The monument assembly includes a plurality of support members connected together and a set of floor fittings connected to the plurality of support members. The set of floor fittings configured to be connected to the vehicle. A plurality of non-loadbearing panels is connected to the plurality of support members. A load path of the monument assembly is carried by the plurality of support members and not the plurality of panels.