Verbundstoff mit thermoplastischer gehärteter novolac-basierter epoxidmatrix
AT1904197TUndetermined Publication Date: 2026-04-15HEXCEL CORP
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Patent Information
- Application Number
- AT2023211855T
- Authority / Receiving Office
- AT · AT
- Patent Type
- Patents
- Current Assignee / Owner
- Priority Date
- 2017-06-14
- Filing Date
- 2017-06-20
- Publication Date
- 2026-04-15
- Estimated Expiration
- 2037-06-20
AI Technical Summary
Technical Problem
Aerospace prepregs face challenges in achieving high tensile and compressive strengths while maintaining high damage tolerance and interlaminar fracture toughness, as increasing modulus for compression strength often reduces damage tolerance and fracture toughness.
Method used
The use of a pre-impregnated composite material with a resin matrix composed of novolac epoxy resin, triglycidyl aminophenol epoxy resin, thermoplastic particles, and a thermoplastic toughening agent, along with a curing agent, which provides a balance between strength and toughness.
Benefits of technology
This formulation results in composite parts with unexpectedly high interlaminar fracture toughness and improved damage tolerance, meeting the stringent requirements for aerospace applications.
✦ Generated by Eureka AI based on patent content.
Abstract
Pre-impregnated composite material (prepreg) that can be cured / molded to form aerospace composite parts. The prepreg includes carbon reinforcing fibers and an uncured resin matrix. The resin matrix includes an epoxy component that is a combination of a hydrocarbon epoxy novolac resin and a trifunctional epoxy resin and optionally a tetrafunctional epoxy resin. The resin matrix includes polyethersulfone as a toughening agent and a thermoplastic particle component.
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