Aircraft Heated Floor Panel Impact Layer for FST and Cut Resistance
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Solution Overview
Problem
Existing impact layers in aircraft heated floor panels face challenges in meeting mechanical strength requirements while adhering to flammability, smoke, and toxicity regulations, often compromising on structural integrity due to resin modifications.
Innovation Solution
A heated floor panel assembly featuring a woven high temperature thermoplastic fiber matrix or composite fiber matrix impregnated with a resin, combined with structural and core layers, and a heating element, which enhances mechanical strength and meets stringent FST requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If resin is modified with additives to meet flammability, smoke, and toxicity requirements, then FST requirements are satisfied, but mechanical strength of the impact layer decreases
Solution Approach 1:
The patent employs a composite fiber matrix consisting of high-temperature thermoplastic fibers combined with other fiber types (such as aramid, glass, or carbon fibers) to create an impact layer that simultaneously achieves both mechanical strength and fire safety. This composite structure allows the material to meet FST requirements while maintaining structural integrity, resolving the contradiction between safety compliance and mechanical performance
Solution Approach 2:
The invention changes the chemical and physical parameters of the resin system by selecting high-temperature thermoplastics with specific molecular structures that inherently provide both fire resistance and mechanical strength. By adjusting fiber composition ratios, resin chemistry, and curing characteristics, the patent optimizes the balance between meeting FST standards and maintaining impact resistance
2Strength
If a woven fiber matrix is used to provide structural integrity, then mechanical strength is improved, but resistance to knife cuts and punctures decreases
Solution Approach 1:
The patent uses a composite fiber matrix combining high-temperature thermoplastic fibers with high-strength fibers such as aramid, glass, or carbon fibers. This composite structure provides both the structural integrity needed for load-bearing and the cut/puncture resistance required for impact protection, as different fiber types contribute complementary mechanical properties
Solution Approach 2:
The invention implements local quality variations within the impact layer by strategically distributing different fiber types and resin formulations in specific regions. Areas requiring higher puncture resistance receive enhanced fiber concentrations or different material compositions, while other regions are optimized for flexibility or thermal properties, creating a spatially differentiated structure that addresses multiple performance requirements simultaneously
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 solution provides a mechanically strong and durable impact layer that surpasses flammability, smoke, and toxicity standards, while maintaining structural integrity and thermal conductivity, ensuring enhanced protection and comfort in aircraft cabins.
Implementation Method 1
a resin infiltrating the woven fiber matrix
Implementation Method 2
The core layer absorbs shear stress
Implementation Method 3
a heating layer between the core layer and the top surface
Data Source
Figure 1
Figure 2.
Figure 3~4
AI summary
A heated floor panel assembly (10) for aircraft includes an impact layer (24) made from a 2-D or 3-D woven high temperature thermoplastic fiber matrix impregnated with a resin. The impact layer (24) can further include woven metallic fibers. The assembly (10) also includes a stack of structural layers (16, 20), a heating layer (22), and a core layer (18) for absorbing shear stress.