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A7075¤»¨¤¾T´Î A7075¶Wµw¾T

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ªF²ð¥«ªF·~¤j©Ýª÷Äݦ³­­¤½¥q±M·~¨ÑÀ³¬ü°êALCOA¡B¶ø¦a§QAMAGµ¥°ê¤§¶i¤f¾T¦Xª÷ªO§÷¡B¶ê´Î (7075¡B6061¡B5052¡BMIC-6¡K)¡C²£«~¼sªxÀ³¥Î©ó¾÷±ñ³]³Æ¡A¥b¾ÉÅéÀ³¥Î¡Bªv¨ã¡B§¨¨ã¡B¹q¤l²£«~µ¥¦h­Ó»â°ì¡C©Ò®w¦sªº¾T¦Xª÷¤Ø¤o¡B³W®æ¡C§Ú¥q¦b¼sªF¬Ù¤º³Æ¦³¤j¶q²{³f2000¾l¾·¡C«ö«È¤á©Ò»Ý¤Ø¤oµô¤Á¤U®Æ¨Ñ³f¡C

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7075¾TªO ¶i¤f¾TªO7075 ¾T¦Xª÷ªO7075 ¾TÁ¡ªO7075 ¶i¤f¦Xª÷¾T7075

7075¾T´Î ¶i¤f¾T´Î7075 ¾T¦Xª÷´Î7075 ¯èªÅ¾T§÷7075 ¶i¤f¾T§÷7075-T6 7075-T651

7075¾T´Î²¤¶¡AAA7075¾T´Î¥Î³~¡AAL7075¾T´Î²£¦Û¬ü¾T

7075¾T´Î­@»G»k¾T¦Xª÷7075¤w³Qµû¦ô¤j®ð­·¤Æ¡AÀ³¤O»G»k¶}µõ©M­é¸¨¦b¥Ø«e©Ò¦³¥i¥ÎªºµÊ®ð¡C³o¨Ç­È¤w³Q¥Î¨Ó§@¬°¸ûªñ´Á°ªªºµo®i¤ñ¸û¼Ð·Ç±j«×¯è¤Ñ¦Xª÷¡C¦b7«Y¦C¦Xª÷¡A©è§Ü¤@¯ë§ðÀ»¡ASCC©M­é¸¨»G»kªº§ïµ½»P°ª®p´Á¬Û¤ñ¡AÅãµÛ¶WÄÖªºµÊ®ð¡]T7±Ò°ÊÃþ«¬¡^¹ê¤OµÊ®ð¡]T6¡^ªº¡C

7075¾T´Î³\¦h¼ö³B²z©M¼ö³B²z¤èªk¥i¥Î¨ÓÃиü¤Uªº¯h³Òµõ¯¾¥Íªø¦æ¬°¥¿¦b¦¨¬°¤é¯q­«­nªº¦Xª÷¯h³ÒÃöÁ䪺¿ï¾Ü­¸¾÷µ²ºc¡C¦UºØ°ª±j«×¯è¤Ñ¦Xª÷­¸¦æ¤p®Éªº¥Í¬¡¤¤¨Ï¥Î¨âºØÃþ«¬ªº¹w´ú¬Û¤ñ¡A¯h³ÒÃÐ;¾÷Ál®ÚÀ³¥Î¡]±i¤O¬°¥D¡^¡A©M¤ô¥­§ÀÁlªºÀ³¥Î¡]©Ô¦ù¡AÀ£ÁY¡^¡C¨î©w¨Îªº±j«×¡A¶´©Ê©M¨ä¥L¥i¨úªº¦r²Å²Återistics¦Xª÷¥¿½TÀ³¥Î7075Á¡ªO©M«pªO²£«~¡C°Ñ·ÓMIL-H6088¡A¾T¼ö³B²z¦Xª÷ªþ¥[«H®§¡C

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Alloy 7075 sheet and plate products have application throughout aircraft and aerospace structures where a combination of high strength with moderate toughness

and corrosion resistance are required.

Typical applications are alclad skin sheet, structural plate components up to 4 inches in thickness and general aluminum

aerospace applications.

CHEMICAL COMPOSITION LIMITS (WT. %)

Si  . . . . . . . . . . .

0.40

Zn . . . . . . . . . . .

5.1-6.1

Fe . . . . . . . . . . .

0.50

Ti . . . . . . . . . . . .

0.20

Cu . . . . . . . . . . .

1.2-2.0

Others, each . . . .

0.5

Mn . . . . . . . . . . .

0.30

Others, total . . . .

0.15

Mg . . . . . . . . . . .

2.1-2.9

Balance, Aluminum

Cr . . . . . . . . . . .

0.18-0.28

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