Prediction of fatigue life of a main landing gear.

The present work focuses on implementing and adapting modelling & analysis via FE based methods for the Aerospace industry components. The hotspots of stress in main landing gear are identified using simulations for different load cases. Another analysis based on Finite Element method is executed to speculate the potential location of initiation of crack with the loads as applied in the repetitive test program. A comparative study is conducted of classical method calculated stress value with software simulation results. The estimation of corresponding fatigue life of main landing gear is also performed. [ABSTRACT FROM AUTHOR]