TY - GEN
T1 - Failure analysis and fatigue life assessment of a redesigned aircraft landing gear component
AU - Panagiotopoulos, D. I.
AU - Stamoulis, K.
PY - 2013/1/1
Y1 - 2013/1/1
N2 - The present study deals with the failure analysis, the redesign and the fatigue life assessment of a rod end component of the North American T-2 jet trainer aircraft, nose landing gear (NLG) system. The rod ends suffer fatigue crack failures under tensile operational loading. Specifically, they are subjected to repeated loads during the take-off and landing of the aircraft which cause nucleation and growth of fatigue cracks. This study has been conducted by combining a finite element analysis (FEA) with a stress-life, fatigue design approach. A new component was designed with optimized geometry and the analysis has shown a significant decrease of maximum stress values, as compared to the corresponding values of the failed component and a subsequent increase in fatigue life without any other change in stress distribution. Furthermore, a specimen of the optimized design was manufactured and tested both functionally and operationally.
AB - The present study deals with the failure analysis, the redesign and the fatigue life assessment of a rod end component of the North American T-2 jet trainer aircraft, nose landing gear (NLG) system. The rod ends suffer fatigue crack failures under tensile operational loading. Specifically, they are subjected to repeated loads during the take-off and landing of the aircraft which cause nucleation and growth of fatigue cracks. This study has been conducted by combining a finite element analysis (FEA) with a stress-life, fatigue design approach. A new component was designed with optimized geometry and the analysis has shown a significant decrease of maximum stress values, as compared to the corresponding values of the failed component and a subsequent increase in fatigue life without any other change in stress distribution. Furthermore, a specimen of the optimized design was manufactured and tested both functionally and operationally.
KW - Aircraft component design
KW - Computational contact mechanics
KW - Engineering
KW - Failure analysis
KW - Fatigue life assessment
KW - Finite element analysis
UR - http://www.scopus.com/inward/record.url?scp=84905705086&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84905705086
SN - 9789608810433
T3 - Engineering Against Failure - Proceedings of the 3rd International Conference of Engineering Against Failure, ICEAF 2013
SP - 838
EP - 844
BT - Engineering Against Failure - Proceedings of the 3rd International Conference of Engineering Against Failure, ICEAF 2013
PB - University of Patras, Laboratory of Technology and Strength of Materials
T2 - 3rd International Conference of Engineering Against Failure, ICEAF 2013
Y2 - 26 June 2013 through 28 June 2013
ER -