Abstract
The carbon fiber/epoxy composite (CFC) T-joints were fabricated and tested to determine their fatigue life under a standard fighter aircraft spectrum load sequence, mini-FALSTAFF with various reference loads. Further, the fatigue life of T-joint subjected to the same spectrum load sequence was predicted. For this purpose, the static pull-out (tension) and push-in (compression) tests were conducted on T-joints. Then, the constant amplitude fatigue tests were conducted to determine the load-life (P–N) curves at three different load ratio, R=Pmin/Pmax of 0.1, −1.0 and 10.0.The static and fatigue test data generated was then employed to construct constant life diagram (CLD) for T-joint. The fatigue damage for each of the rain flow counted load cycle of mini-FALSTAFF spectrum load sequence was determined using CLD. Using linear damage accumulation theory, the fatigue life of T-joint was estimated. The predicted fatigue life was observed to agree quite well with experimental results.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
