Advanced Composites Prepreg - Nominal 250 °F Cure - Carbon Fiber and Epoxy Resin, Unidirectional Tape
- Aerospace Material Specification
- AMS3960
- Issued
Scope
Rationale
Recommended Content
Aerospace Material Specification | 350 °F Autoclave Cure, Low Flow Toughened Epoxy Prepregs, Type 35, Class 1, Grade 190, Fiber 2 |
Aerospace Material Specification | 350 °F Autoclave Cure, Low Flow Toughened Epoxy Prepregs, Type 35, Class 1, Grade 190, Fiber 1 |
Aerospace Material Specification | Organic Fiber (Para-Aramid), Yarn and Roving, High Modulus |
Topic
Data Sets - Support Documents
Title | Description | Download |
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Unnamed Dataset 1 | ||
Unnamed Dataset 2 | ||
Unnamed Dataset 3 | ||
TABLE 1 | ||
TABLE 2 | ||
TABLE 3 | UNCURED PREPREG PHYSICAL AND CHEMICAL PROPERTIES | |
TABLE 4 | CURED LAMINA PHYSICAL PROPERTIES | |
TABLE 6 |
Issuing Committee
AMS P17 Polymer Matrix Composites Committee
AMS P-17, Polymer Matrix Composites, is a technical committee in SAE’s Aerospace Materials Systems Group with the responsibility to develop and maintain material specifications and other SAE technical reports for composite materials, including prepregs, reinforcing fibers and fabrics, matrix resins, adhesives, and core materials. The committee works in conjunction with related bodies such as the Composite Materials Handbook -17 (CMH-17), ASTM Committee D30 on Composite Materials, the National Center for Advanced Materials Performance (NCAMP), the Performance Review Institute (PRI), and regulatory authorities such as FAA and EASA.