China Aircraft Aerospace Aluminum Alloy Plate for Fuselage Frame/Wing Skin/Bulkhead/Flange, Find details about China Aircraft Aluminum Alloy Plate for Fuselage Frame, Aerospace Aluminum Alloy Plate for Wing Skin from Aircraft Aerospace Aluminum Alloy Plate for Fuselage Frame/Wing Skin/Bulkhead/Flange
| Chemical Composition of 7010 Alloy | |||||||||||||
| Alloy | Si | Fe | Cu | Mn | Mg | Cr | Ni | Zn | Ti | Zr | Others | Al | |
| Each | Total | ||||||||||||
| 7010 | 0.12 | 0.15 | 1.5~2.0 | 0.1 | 2.1~2.6 | 0.05 | 0.05 | 5.7~6.7 | 0.05 | 0.10~0.16 | 0.05 | 0.15 | Remainder |
| Alloy | Alloy sereis | Main features | σb Value/MPa | Working Temperature/ºC |
| 7010 | 7000 series | 7010 and 7050 basic properties of the alloy, the main varieties of thick plate, use T7351, T7451, T7651. | 414~524 | <125 |
| Physical Property of 7010 Alloy | |||||||||
| Alloy | Type | Temper | /mm | Direction | σb/MPa | σp 0.2/MPa | δ % | KIC or KC | |
| 7010 | Aluminum plate | T7651 | ~.50.80 | L | 524 | 455 | 8 | δ25~51MM: L -T: 27.5; T-L: 25.3; >δ51~76MM L -T: 26.4; T - L: 24.2; S-T: 22.0 >δ76~126MM L -T: 24.0; T - L: 22.0; S-T:19.8 >δ127~140MM L -T: 22.0; T - L: 19.8; S-T:18.7 | |
| LT | 524 | 455 | 6 | ||||||
| >δ50.80~63.50 | L | 517 | 448 | 8 | |||||
| LT | 517 | 448 | 6 | ||||||
| ST | 490 | 407 | 2.5 | ||||||
| >δ63.50~76.20 | L | 503 | 441 | 7 | |||||
| LT | 510 | 441 | 5 | ||||||
| ST | 483 | 400 | 2.5 | ||||||
| >δ76.20~101.60 | L | 496 | 441 | 7 | |||||
| LT | 503 | 434 | 5 | ||||||
| ST | 476 | 386 | 2 | ||||||
| >δ101.60~127.0 | L | 496 | 434 | 7 | |||||
| LT | 496 | 427 | 5 | ||||||
| ST | 469 | 379 | 2 | ||||||
| >δ127.0~139.7 | L | 490 | 427 | 6 | |||||
| LT | 496 | 421 | 4 | ||||||
| ST | 455 | 365 | 2 | ||||||
| Aluminum plate | T7451 | ~.50.80 | L | 490 | 427 | 9 | |||
| LT | 496 | 427 | 6 | ||||||
| >δ50.80~63.50 | L | 490 | 427 | 9 | |||||
| LT | 496 | 427 | 6 | ||||||
| ST | 462 | 393 | 2.5 | ||||||
| >δ63.50~101.60 | L | 483 | 421 | 9 | |||||
| LT | 490 | 421 | 6 | ||||||
| ST | 455 | 386 | 2 | ||||||
| >δ101.60~127.0 | L | 469 | 407 | 9 | |||||
| LT | 476 | 407 | 5 | ||||||
| ST | 448 | 372 | 2 | ||||||
| >δ127.0~139.7 | L | 455 | 393 | 8 | |||||
| LT | 462 | 393 | 5 | ||||||
| ST | 434 | 365 | 2 | ||||||
| 7010 | Aluminum plate | T7351 | ~.50.80 | L | 462 | 379 | 9 | ||
| LT | 469 | 379 | 7 | ||||||
| >δ50.80~76.0 | L | 462 | 379 | 9 | L -T: 31.9; T - L: 28.6; S-T:25.3 | ||||
| LT | 469 | 379 | 7 | ||||||
| ST | 434 | 338 | 3 | ||||||
| >δ76.0~101.60 | L | 445 | 372 | 9 | |||||
| LT | 462 | 372 | 7 | ||||||
| ST | 427 | 331 | 3 | ||||||
| >δ101.60~127.0 | L | 448 | 365 | 9 | L -T: 28.6; T - L: 26.4; S-T: 24.2 | ||||
| LT | 455 | 365 | 6 | ||||||
| ST | 420 | 324 | 3 | ||||||
| >δ127.0~139.7 | L | 440 | 358 | 9 | |||||
| LT | 448 | 358 | 5 | ||||||
| ST | 414 | 317 | 3 | ||||||
| Alloy | Temper | Aircraft model | Application parts and typical parts |
| 7010 | Aluminum plate: T7651,T7451,T7351 | A320 | The thick section of the main structure of high load, such as the manufacture of fuselage frame and bulkhead, wing skin, extrusion reinforcing rod, stringers and ribs, forging parts, gear support member, beams, strengthening panels, flanges, important joints etc.. |