Composite Aircraft Opening Reinforcement via Co-cured Perimetral Element
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Solution Overview
Problem
In aircraft fuselage structures made of composite materials, large openings weaken the structure and require additional reinforcement, which increases weight and costs due to the need for multiple parts and labor-intensive assembly, whereas existing solutions involve frame-like structures with riveted joints and increased skin thickness.
Innovation Solution
A reinforcing structure comprising an integral one-piece perimetral element along the opening edge, paired longitudinal reinforcing elements with increased thickness, and transverse reinforcing elements that reproduce the primary structure's geometry, integrated through co-bonding or co-curing, eliminating the need for additional parts and joints.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If frame-like structures with riveted joints and increased skin thickness are used to reinforce large openings, then structural strength is improved, but weight and manufacturing complexity increase
Solution Approach 1:
The patent merges the reinforcement elements with the skin by co-bonding or co-curing them as an integrated composite structure. This eliminates separate riveted joints and multiple discrete parts, combining the skin and reinforcement into a unified structure that maintains strength while reducing weight and manufacturing complexity.
Solution Approach 2:
The patent uses composite materials for the reinforcement structure, specifically co-bonding or co-curing composite reinforcement elements with the composite skin. This allows the reinforcement to be as lightweight as the skin itself while providing the necessary structural strength, unlike traditional metal reinforcement that would increase weight.
2Strength
If frame-like structures with riveted joints are used to reinforce large openings, then structural strength is improved, but manufacturing costs and assembly labor increase
Solution Approach 1:
The patent combines the reinforcement elements with the skin into a single integrated component manufactured through co-bonding or co-curing processes. This eliminates the need for separate assembly steps involving riveted joints, reducing both manufacturing complexity and labor requirements while maintaining structural integrity.
Solution Approach 2:
The reinforcement elements are pre-positioned and integrated with the skin during the manufacturing process itself, rather than being added as separate assembly steps afterward. This preliminary integration simplifies manufacturing by combining operations and reducing the number of discrete steps required.
3Reliability
If multiple discrete parts and joints are used to reinforce openings, then structural coverage is improved, but device complexity increases
Solution Approach 1:
The patent merges multiple discrete reinforcement parts into a single integrated reinforcement structure that is co-bonded or co-cured with the skin. This unified structure provides complete structural coverage around the opening while eliminating the complexity of assembling multiple separate components with riveted joints.
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 solution enhances structural efficiency and reduces costs by integrating reinforcement directly into the manufacturing process, optimizing weight and eliminating manual assembly complexities, while providing sufficient strength and buckling resistance for large openings.
Implementation Method 1
The perimetral reinforcing element along the edge of the opening (10) is obtained, integrated and as one piece, during the associated process for manufacture of the skin (2), by means of co-bonding or co-curing
Implementation Method 2
by means of co-bonding or co-curing
Data Source
Figure 1a~1b
Figure 2~3a
Figure 3b~3c
AI summary
Reinforcement structure (1) for an opening (10) in the primary structure of an aircraft, said structure comprising a skin (2), frame members (3) which are transverse with respect to the flying direction of the aircraft, and stringers (4) which are longitudinal with respect to the flying direction of the aircraft, said reinforcing structure (1) comprising: - a perimetral reinforcing element (5) situated along the edge of the opening (10) and reproducing the geometrical form thereof; - at least one pair of transverse reinforcing elements (6) arranged on both transverse sides of the opening (10); - at least one pair of longitudinal reinforcing elements (7) arranged on both longitudinal sides of the opening (10).