CNT-Infused Composite Forming Tool for Aircraft Surface Precision
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Solution Overview
Problem
Current aircraft article forming tools face limitations in producing smooth aerodynamic surfaces, leading to suboptimal laminar airflow and increased fuel consumption, due to material and manufacturing constraints, including thermal expansion issues and susceptibility to scratches.
Innovation Solution
A composite forming tool with a forming surface infused with carbon nano tubes (CNTs) provides a hard and smooth surface, reducing thermal expansion and scratch resistance, while enabling efficient production of large-scale and complex aircraft components with optimal laminar airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If traditional resin matrix materials are used for forming tools, then the tool can be easily manufactured, but the forming surface cannot achieve high smoothness and scratch resistance
Solution Approach 1:
The patent applies composite materials by infusing carbon nanotubes (CNTs) into the resin matrix of the forming tool. This creates a hybrid material system where CNTs provide enhanced surface smoothness, hardness, and scratch resistance, while the resin matrix maintains ease of manufacture and structural integrity. The composite structure resolves the contradiction by combining materials with complementary properties.
Solution Approach 2:
The patent changes the physical and chemical parameters of the resin matrix by incorporating nanoscale carbon tubes. This modification alters the surface properties (smoothness, hardness) and mechanical properties (scratch resistance) of the forming tool without fundamentally changing the manufacturing process. The parameter change approach allows achieving high surface quality while maintaining manufacturing feasibility.
2Strength
If the forming surface is made harder to prevent scratches, then scratch resistance improves, but thermal expansion issues worsen
Solution Approach 1:
The carbon nanotube-resin composite creates a material system where CNTs provide hardness and scratch resistance, while the resin matrix maintains favorable thermal expansion characteristics. The composite structure allows the tool to resist scratches through CNT reinforcement while the overall material composition retains low thermal expansion properties suitable for precision forming applications.
3Ease of manufacture
If conventional forming tools are used, then production cost is low, but fuel consumption increases due to suboptimal laminar airflow
Solution Approach 1:
The patent addresses airflow characteristics by creating a forming tool surface that enables optimal laminar flow conditions. The CNT-infused surface provides the smoothness required for laminar airflow over aircraft surfaces, reducing drag and fuel consumption. This connects surface quality to aerodynamic performance and energy efficiency.
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
The CNT-infused forming tool ensures a smooth outer surface of aircraft articles, reducing fuel consumption, enhancing mechanical strength, and allowing for faster curing times, while being cost-effective and environmentally friendly.
Implementation Method 1
decrease the problem with thermal expansion of the forming tool's forming surface
Implementation Method 2
The hardness of the forming surface prevents that no scratches of the forming tool's forming surface will be made
Data Source
Figure 1a~3b
Figure 4~6
Figure 7a~9
AI summary
The present invention regards an aircraft article composite forming tool (3) and a method for producing the tool (3), the aircraft article (2) to be formed comprises a composite material including an outer surface (9), the aircraft 5 article composite forming tool (3) comprises a matrix laminate (11) made of at least an upper ply (P1) including a forming surface (7) for forming said aircraft article (2) and outer surface (9). The upper ply (P1) comprises a nano filament structure (15) embedded 10 therein.