STATE-OF-THE-ART FINITE ELEMENT MODELING OF ROTORCRAFT MAIN ROTOR BLADE ROOT END FOR BIRD STRIKE DAMAGE ANALYSIS

摘要

This paper demonstrates the state-of-the-art composite modeling methodology to investigate thernbird strike phenomenon using available numerical bird models through experimental tests andrnsimulation tools. The present work is based on the application of non-linear explicit finite elementrnanalysis to simulate the response of rotorcraft main rotor blade root end under high velocity impactrnload. The damage behavior of blade under soft body impact depends upon bird size, blade size,rnblade span wise location of impact and bird orientation with respect to hitting location, bladernrotational speed and rotorcraft cruise speed. Bird model is considered as hydrodynamic with lengthrnto diameter ratio of 2. A bird strike event is characterized by loads of high intensity and shortrnduration. A transient explicit non-linear finite element based impact analysis using Autodyn hasrnbeen carried out to predict bird strike resistance to withstand 1.0 kg bird at critical flight condition.rnNumerical analysis indicates that blades do not tear which agrees well with the physical testrnconducted.