Integrated Aircraft Structure Reinforcing Elements
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft structures with openings or subjected to high loads face challenges in achieving strength, stiffness, and weight savings due to high production costs and debonding risks associated with traditional reinforcement methods using mechanical attachments.
Innovation Solution
The integration of omega-shaped or T-shaped composite material stringers and frames with inner and outer reinforcing elements that are manufactured together without mechanical attachments, ensuring continuous load transfer and eliminating the need for rivets and extra parts.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional reinforcement methods using mechanical attachments (rivets or bonded connecting elements) are used at crossing zones, then the structure can support high loads and maintain strength, but the weight increases and debonding risks arise
Solution Approach 1:
The patent merges the stringer and frame into a single continuous composite element that passes through the opening. This integration eliminates the need for separate connecting elements (rivets or bonds) at crossing zones, thereby reducing weight while maintaining load-bearing capacity. The continuous element distributes loads uniformly across the structure without concentration points.
2Strength
If traditional reinforcement methods using mechanical attachments are used at crossing zones, then the structure can withstand high loads, but production costs and assembly costs increase
Solution Approach 1:
By combining the stringer and frame into a single integrated composite element, the patent reduces the number of manufacturing steps and assembly operations. The continuous element can be manufactured as one piece using composite material forming processes, eliminating the need for separate riveting or bonding operations, thus reducing both production and assembly costs.
Solution Approach 2:
The patent extracts the mechanical attachment elements (rivets and bonded connecting elements) from the structure entirely. By using a continuous composite element that inherently provides structural reinforcement, the patent eliminates the need for these additional components and their associated manufacturing and assembly processes.
3Strength
If traditional reinforcement methods using bonded connecting elements are used at crossing zones, then the structure can support high loads, but debonding risks increase
Solution Approach 1:
The patent merges the stringer and frame into a single continuous composite element, eliminating the need for bonded connections. This integration removes the interface between separate elements where debonding could occur, thereby improving reliability while maintaining load-bearing capacity through the continuous nature of the composite structure.
Data Source
AI summary
The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.