Blended Wing Body Composite Assembly for Delamination Resistance
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Solution Overview
Problem
Conventional aircraft structures face issues with delamination and binding composite materials, limiting their use on outer surfaces.
Innovation Solution
A composite assembly is created by molding first and second assemblies with fibers infused with resins, and a joining region where fibers from both assemblies are embedded in a single resin matrix, forming a unified structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional aircraft use aluminum or aluminum mixtures for the outer surface, then the structure is easy to manufacture and has good binding properties, but the structure suffers from delamination issues and lacks the durability of composite materials
Solution Approach 1:
The patent merges multiple fiber assemblies into a single unified composite structure by embedding fibers from different assemblies into a continuous resin matrix. This combining approach eliminates delamination between separate components while maintaining the manufacturing advantages of modular assembly processes.
Solution Approach 2:
The invention uses composite materials consisting of multiple fiber types (e.g., carbon fiber, glass fiber) embedded in a resin matrix to create a unified structure. This composite approach provides both the durability and delamination resistance of integrated composites while allowing modular manufacturing of individual fiber assemblies before final consolidation.
2Strength
If composite materials are used for aircraft outer surfaces, then delamination and binding issues occur, but composite materials offer superior strength and durability
Solution Approach 1:
The patent combines multiple fiber assemblies into a single integrated composite structure where fibers from different assemblies are embedded together in a continuous resin matrix. This merging eliminates the delamination problems that occur between separately bound composite components while maintaining the high strength characteristics of composite materials.
Solution Approach 2:
The invention creates a homogeneous resin matrix that uniformly embeds fibers from multiple assemblies, ensuring consistent bonding and eliminating weak interfaces. This homogeneous integration prevents delamination by creating a unified composite structure rather than layered assemblies with potential separation planes.
3Stability of the object's composition
If multiple fiber assemblies are joined together, then a unified structure is achieved, but the joining process increases manufacturing complexity
Solution Approach 1:
The patent prepares fiber assemblies in advance with pre-positioned fibers and predetermined orientations before the final joining process. This preliminary preparation simplifies the subsequent consolidation process by reducing the complexity of aligning and integrating multiple assemblies during final manufacturing.
Solution Approach 2:
The invention uses a resin matrix as an intermediary material that facilitates the joining of multiple fiber assemblies. The resin acts as a bonding medium that integrates separate assemblies into a unified structure, simplifying the joining process by providing a continuous matrix that automatically bonds fibers from different assemblies without requiring complex mechanical fastening or additional joining steps.
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 minimizes delamination and tearing, enabling a single unified structure for aircraft components, enhancing structural integrity and durability.
Implementation Method 1
a joining region including at least a first portion of the first plurality of fibers and at least a first portion of the second plurality of fibers embedded within a single resin matrix
Implementation Method 2
the at least a first portion of the first plurality of fibers and the at least a first portion of the second plurality of fibers are infused with a third resin
Data Source
AI summary
A composite assembly for a blended wing body aircraft, the composite assembly comprising a first assembly comprising a first molded part, wherein the first molded part comprises a first plurality of fibers, the first molded part partially infused with a first resin, a second assembly oriented relative to the first assembly, the second assembly comprising a second molded part wherein the second molded part comprises a second plurality of fibers, the second molded part partially infused with a second resin, and a joining region, the joining region comprising at least a portion of first plurality of fibers and at least a portion of second plurality of fibers, the at least a portion of first plurality of fibers and the at least a portion of second plurality of fibers substantially adjacent and infused with a third resin.