| Description |
xi, 88 leaves : illustrations ; 28 cm. |
| Summary |
"This thesis presents the results of the research conducted to determine the effects of corrosion on fatigue life of 2024-T3 clad aluminum alloy riveted lap joints, similar to those found on an aircraft fuselage structure. Because of the adverse environment in which an aircraft operates, corrosion is induced on its structure while fatigue loading occurs due to pressurization cycles, take-off and landing, and air-borne maneuvers. Single, double and triple column, 3-rows riveted lap joint specimens were fabricated and corroded in a Q-Fog accelerated corrosion chamber for five months using ASTM G85-A5 Prohesion test. Specimens were taken out of the chamber every four weeks and corrosion products deposited on them were removed by immersion in concentrated nitric acid, with consequent determination of mass loss and corrosion rate for each specimen. The specimens were later fatigue loaded to failure on MTS 880 Universal Testing Machine with acoustic emission monitoring, which detected failure. Results indicate that exposure of lap joint specimens to corrosive environment increases corrosion, corrosion rate and significantly reduce fatigue life"--Abstract, leaf iv. |
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