Al-si-mg aluminum alloy aircraft structural component production method
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United States of America Patent
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N/A
Issued Date -
Feb 7, 2002
app pub date -
Apr 5, 2001
filing date -
Apr 7, 2000
priority date (Note) -
Abandoned
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Abstract
An aircraft structural component, particularly a fuselage component, production method using rolled, extruded or forged products made of aluminum alloy with the following composition (% by weight): Si: 0.7-1.3; Mg: 0.6-1.1; Cu: 0.5-1.1; Mn: 0.3-0.8; Zn<1; Fe<0.30; Zr<0.20; Cr<0.25; other elements <0.05 each and <0.15 in total; remainder aluminum. The product is treated by steps of: solution heat treatment of the product between 540 and 570.degree. C.; quenching the solution heat treated product; producing the structural component by forming of the product, and welding if required; ageing of the structural component, in one or more stages, for which the total equivalent time at 175.degree. C. expressed in hours is between (-160+57.gamma.) and (-184+69.gamma.), .gamma. being the sum of Si+2Mg+2Cu contents in % by weight. The invention results in an improvement in tolerance to damage with no loss of other operating parameters.
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