AS4 (Hercules) carbon fibre (12,000-filament tow) in a 3502 (Hercules) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. Surface-treated.
Compliance & Regulations
Fiber Direction
Ply Schedule
Laminate Code
[0/0/0/0/0/0/0/0]s
Fiber angles relative to the 0° reference direction (red arrow in 3D view). 0° = longitudinal, 90° = transverse, ±45° = shear paths.
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Compressive Modulus(Ec) | 970 – 20,600 | ksi | 8 entriesClick to expand | ||
Compressive Strength(σc) | 15.30 – 252 | ksi | 18 entriesClick to expand | ||
Shear Modulus(G)4 entries | 543 range 496–593n=33, 5 batches, CV 5.16% | ksi | 24°C · RTA · 12-axis · [+-45]:4s · as-measured | ||
| ↳ | 769 range 738–863n=23, 5 batches, CV 3.69% | ksi | -54°C · CTA · 12-axis · [+-45]:4s · as-measured | ||
| ↳ | 217 range 169–260n=33, 5 batches, CV 9.25% | ksi | 82°C · ETW · 12-axis · [+-45]:4s · as-measured | ||
| ↳ | 141 range 103–205n=41, 5 batches, CV 17.9% | ksi | 121°C · ETW · 12-axis · [+-45]:4s · as-measured | ||
Ultimate Shear Strength(Fsu) | 10.30 – 16.20 | ksi | 7 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 1.650 – 317 | ksi | 20 entriesClick to expand | ||
Young's Modulus(E) | 910 – 23,900 | ksi | 8 entriesClick to expand | ||