Staggered Comb Composite Reinforcement for Aircraft Intersection Strength
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Solution Overview
Problem
Conventional composite materials used in aircraft components, such as flaps and wing structures, lack sufficient out-of-plane strength at intersection regions, leading to high manufacturing costs, weight, and complexity due to the need for separate reinforcement measures.
Innovation Solution
A composite reinforcement component with staggered comb components, forming a cruciform shape, which is manufactured integrally with the main composite structure, eliminating the need for additional reinforcement and reducing out-of-plane loading by allowing force flows on straight paths.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional composite materials are used in aircraft components, then manufacturing is simplified, but out-of-plane strength at intersection regions is insufficient
Solution Approach 1:
The reinforcement component is divided into multiple comb components with staggered teeth that can be assembled together to form an integrated structure. This segmentation allows for easier manufacturing of individual components while achieving the required out-of-plane strength through their combined interlocked configuration
Solution Approach 2:
The invention uses composite materials with specific fiber orientations arranged in comb components to achieve enhanced out-of-plane strength. The staggered comb teeth configuration allows fibers to be optimally oriented for load transfer in multiple directions, providing both strength and manufacturing efficiency
2Strength
If separate reinforcement measures are added to improve structural integrity, then strength is improved, but weight and manufacturing cost increase
Solution Approach 1:
The reinforcement function is merged into the main composite structure through the comb component design. The staggered comb teeth are integrated directly into the structural elements, eliminating the need for separate reinforcement measures and reducing overall weight while maintaining structural integrity
Solution Approach 2:
The comb component structure provides self-reinforcement through its interlocked staggered teeth configuration. The design inherently provides the necessary structural integrity without requiring additional external reinforcement elements, thereby reducing weight
3Strength
If metal materials are used to carry loads in three dimensions, then out-of-plane strength is improved, but manufacturing complexity and weight increase due to required cutouts and reinforcement measures
Solution Approach 1:
The invention uses composite materials with strategically oriented fibers in comb components to achieve three-dimensional load carrying capacity without the need for metal cutouts or additional reinforcement. The fiber orientations are designed to follow force flow paths, providing equivalent or superior performance to metal while maintaining manufacturing simplicity
Solution Approach 2:
The comb component design adds a dimensional aspect to the composite structure by creating staggered teeth that extend in multiple directions. This dimensional configuration allows the composite material to carry loads in three dimensions by distributing forces through the staggered comb structure, eliminating the need for traditional metal reinforcement methods
Data Source
Figure 1(a)~1(b)
Figure 2
Figure 3
AI summary
The present invention pertains to a composite reinforcement component for an aircraft or spacecraft, comprising a first element assembly being aligned in a first plane of extension, and a second element assembly being aligned in a second plane of extension generally perpendicular to the first plane of extension, the second element assembly intersecting the first element assembly at a line of intersection of the first and second planes of extension. The first and second element assembly each comprise at least one pair of staggered comb components, each of the comb components including a base portion and a plurality of generally rectangular protrusions extending coplanar from the respective planes of extension of the respective element assembly. The rectangular protrusions thereby form comb teeth portions of one comb component of the pairs of comb components which are overlapping with comb teeth portions of the other comb component of the pairs of comb components. The comb teeth portions of the first element assembly are offset along the line of intersection by a single comb tooth width with respect to the comb teeth portions of the second element assembly.