Finite element modeling and fatigue life prediction of helicopter composite tail structure under multipoint coordinated loading spectrum

This paper presents a numerical study on fatigue life prediction of helicopter composite tail structure under multipoint coordinated loading spectrum. The FE model full-scale was established and then validated with the experimental results strain displacement distributions. Good agreement has been achieved between simulation experiments two static conditions representing left yawing two-point horizontal landing. A progressive damage analysis performed spectrum loading. predicted is 64 repeated applications load No element failure after 48 impact introduced left-side wall thereafter propagated another 6 spectrum, which agrees well observations. shown to be practical engineering tool for structures.