کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
781723 | 1463856 | 2006 | 7 صفحه PDF | دانلود رایگان |
![عکس صفحه اول مقاله: Fatigue test of lightweight composite wing structure Fatigue test of lightweight composite wing structure](/preview/png/781723.png)
Fatigue tests of hat-shape stringer stiffened panel are conducted, where this panel is a typical part of upper skin of lightweight composite wing using new production technology of stitching, co-bonding and RTM method. Impact damages are applied on skin/stringer co-bonded part and typical skin part of the test panel by drop-weight impact machine. There are two phases in the present test. The first phase is fatigue tests to verify durability of the structure with barely visible impact damages. The second phase is flaw growth tests for evaluation of visible impact damage growth to estimate inspection intervals. The Mini-TWIST (shortened version of The Transport WIng STandard load program) spectrum loading is used for both tests. Non-destructive inspection is carried out by pulsed thermography during the test to observe damage propagation. Finally, static load is applied up to design limit load to verify the residual strength after all the spectrum loading tests.
Journal: International Journal of Fatigue - Volume 28, Issue 10, October 2006, Pages 1109–1115