Composite Window Coaming Adhesion Fuselage Assembly
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Solution Overview
Problem
The existing methods for mounting window frames on aircraft fuselages are costly, time-consuming, and prone to imprecision due to the need for multiple fastening elements and temporary positioning means, which can lead to mechanical integrity and aerodynamic profile issues.
Innovation Solution
A method involving the use of composite materials for frames and fuselage skins, where a glue film is applied between the frame and skin, followed by a co-gluing phase in an autoclave, and a machining phase to form window openings, with a centering unit for precise positioning and reduced fastening elements, allowing for efficient and precise assembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple fastening elements and temporary positioning means are used for mounting window frames, then mechanical integrity is ensured, but assembly time increases and manufacturing costs rise
Solution Approach 1:
The patent combines multiple fastening elements and positioning means into a single integrated frame structure. The frame incorporates built-in positioning features and fastening mechanisms that work together as one unified component, eliminating the need for separate temporary positioning means and multiple discrete fastening elements, thus reducing assembly time while maintaining mechanical integrity
Solution Approach 2:
The frame is pre-configured with integrated positioning features and fastening mechanisms during manufacturing. This preliminary action ensures that when the frame is installed, the positioning and fastening functions are already built-in, eliminating the need for additional assembly steps involving separate positioning means and multiple fastening operations
2Reliability
If multiple fastening elements are used for mounting window frames, then mechanical integrity is ensured, but the number of parts and complexity increases
Solution Approach 1:
The patent merges multiple fastening elements into a single integrated frame structure. The frame incorporates built-in fastening mechanisms that perform the function of multiple separate fastening elements, thereby reducing the total number of parts while ensuring mechanical integrity through the unified design
Solution Approach 2:
The frame is designed as a multi-functional component that simultaneously provides structural support, positioning, and fastening functions. This universal design eliminates the need for multiple specialized parts, reducing complexity while maintaining the mechanical integrity that would otherwise require multiple dedicated fastening elements
3Reliability
If traditional mounting methods are used with multiple components, then mechanical integrity can be achieved, but weight of the installation increases
Solution Approach 1:
The patent combines multiple separate components (frame, fastening elements, positioning means) into a single integrated structure. This merging eliminates the need for multiple discrete parts, reducing the total material used and consequently the weight of the installation, while maintaining mechanical integrity through the unified design
Solution Approach 2:
The integrated frame performs multiple functions (structural support, positioning, fastening) that would otherwise require separate components. This multi-functionality reduces the total number of parts and material consumption, leading to weight reduction while ensuring mechanical integrity through the consolidated design
4Manufacturing precision
If temporary positioning means are used during assembly, then positioning precision can be achieved, but assembly process complexity increases
Solution Approach 1:
The frame is pre-configured with built-in positioning features during manufacturing. These features are integrated into the frame structure itself, eliminating the need for separate temporary positioning means. The positioning function is performed automatically by the frame's own geometry, simplifying the assembly process while maintaining positioning precision
Solution Approach 2:
The frame's built-in positioning features enable the frame to position itself during assembly without requiring external temporary positioning means. The self-positioning capability is achieved through the frame's integrated geometric features, reducing assembly process complexity while ensuring positioning precision
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
This method reduces manufacturing, assembly, and maintenance costs by simplifying the mounting process, improving precision, and minimizing weight, while ensuring mechanical integrity and aerodynamic compatibility.
Implementation Method 1
a glue film is injected in a preparation phase on the interface between a substantially plan external side of the frame crown and the internal side of the skin
Implementation Method 2
The so-assembled unit is introduced into an enclosure, in general an autoclave, to perform a co-gluing phase combining the gluing of the frames and the skin baking in determined conditions of time, temperature and pressure
Implementation Method 3
The so-assembled unit is introduced into an enclosure, in general an autoclave, to perform a co-gluing phase combining the gluing of the frames and the skin baking in determined conditions of time, temperature and pressure
Data Source
AI summary
A reduction of the multiple costs of manufacture, assembly use, and upkeep connected with the assembly of window frames on aircraft fuselages. To this end, the invention provides a particular shape for the frames connected to the fuselage skin according to a specific assembly method. The shape enables, among other things, the window frames to be fitted onto the skin by means of adhesion and also frames to be dispensed with between the fuselage and the window. In one embodiment, composite material window frame has a wall totally in the shape of a crown that is connected, through co-adhesion, to the inner surface of the fuselage skin, also made of composite material. The skin is cut into a window-receiving opening, and the frame has a T-shaped cross section, wherein the bar of the “T” that forms the crown includes two portions having substantially equal lengths “T.”