Composite Part Manufacturing Using Amorphous Outer Layers
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Solution Overview
Problem
Current methods for manufacturing composite aeronautical parts with thermoplastic matrices are technologically complex and economically costly due to the need for high temperatures and controlled cooling rates, especially for semi-crystalline materials like PEEK, which require expensive equipment and materials.
Innovation Solution
A method involving a laminate structure with a semi-crystalline thermoplastic core layer and amorphous thermoplastic outer layers, where the stack is rapidly heated above the glass transition temperature of the amorphous layer but below the melting point of the semi-crystalline layer, allowing for compaction without melting the semi-crystalline resin, and then cooled without controlled cooling, simplifying the process and reducing costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If high consolidation temperature (above 350°C for PEEK) is used for semi-crystalline thermoplastic composites, then compaction and consolidation are achieved, but energy cost and equipment cost increase significantly
Solution Approach 1:
The patent changes the thermal parameters by using a two-layer structure with different glass transition temperatures. The first layer has Tg around 80-120°C and the second layer has Tg around 140-180°C, allowing consolidation at much lower temperatures (below 100°C) compared to conventional semi-crystalline thermoplastics requiring temperatures above 350°C.
Solution Approach 2:
The patent employs a composite preimpregnated material consisting of two different thermoplastic resin layers with distinct glass transition temperatures. This composite structure enables differential softening behavior during heating, allowing the first layer to become tacky and promote bonding at lower temperatures while the second layer remains structurally intact.
2Strength
If high consolidation temperature is used for semi-crystalline thermoplastic composites, then consolidation is achieved, but equipment cost and material requirements increase
Solution Approach 1:
The patent changes the thermal parameters by using a two-layer structure with different glass transition temperatures. The first layer has Tg around 80-120°C and the second layer has Tg around 140-180°C, allowing consolidation at much lower temperatures (below 100°C) compared to conventional semi-crystalline thermoplastics requiring temperatures above 350°C.
Solution Approach 2:
The patent employs a composite preimpregnated material consisting of two different thermoplastic resin layers with distinct glass transition temperatures. This composite structure enables differential softening behavior during heating, allowing the first layer to become tacky and promote bonding at lower temperatures while the second layer remains structurally intact.
3Stability of the object's composition
If controlled cooling rate is applied to semi-crystalline thermoplastic composites, then correct degree of crystallinity is obtained, but process complexity and time increase
Solution Approach 1:
The patent changes the thermal parameters by using a two-layer structure with different glass transition temperatures. The first layer has Tg around 80-120°C and the second layer has Tg around 140-180°C, allowing consolidation at much lower temperatures (below 100°C) compared to conventional semi-crystalline thermoplastics requiring temperatures above 350°C.
4Productivity
If rapid heating is used to reach working temperature quickly, then productivity increases, but risk of thermal damage increases
Solution Approach 1:
The patent applies local quality by creating a two-layer structure where each layer has different thermal properties. The first layer with lower Tg (80-120°C) softens first and provides protective tackiness, while the second layer with higher Tg (140-180°C) remains more rigid during rapid heating, preventing thermal damage to the fiber-matrix interface.
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 reduces operational complexity and costs by minimizing the temperature requirements for compaction and eliminating the need for controlled cooling, while maintaining mechanical properties comparable to conventional composites, with improved interlaminar shear properties.
Implementation Method 1
rapidly heating the stack of plies until a working temperature Tw which is above the glass transition temperature Tg of the amorphous thermoplastic resin but below the melting point Tf of the semi-crystalline thermoplastic resin is reached
Data Source
Figure 1~3
AI summary
Method for manufacturing a composite part, comprising: preparing a stack of plies (30) made of a starting material, applying a vacuum bag (40) to the stack of plies (30), and subjecting the stack of plies (30) to a temperature and pressure cycle in an autoclave. The starting material is a laminate material (1) comprising a resin matrix reinforced with a fibre material, wherein the matrix comprises a core layer (11) of semi-crystalline thermoplastic resin and a pair of outer layers (12, 13) arranged on opposite sides of the core layer (11), each outer layer consisting of amorphous thermoplastic resin, wherein the glass transition temperature Tg of the amorphous thermoplastic resin is below the melting point Tf of the semi-crystalline thermoplastic resin. The temperature cycle in an autoclave comprises: heating rapidly the stack of plies (30) to a working temperature Tw above Tg but below Tf, keeping the stack of plies (30) at the working temperature Tw during a time period for compaction alone; and cooling the stack of plies (30).