The work aims to reveal the damage failure law of the adhesive interface structure of a motor(SRM)under ten-sile loading and the effect of typical parameters on the damage failure process.Based on the established micro finite element model of the adhesive interface structure for nitrate ester plasticized polyether(NEPE)propellant with prefabricated macro-scopic crack,numerical simulation calculations were carried out under three forms of cohesive failure in the propellant,propel-lant/liner adhesive interface debonding,and mixed failure.Then,the crack propagation law under each form of damage and the effects of the matrix strength,particle/matrix adhesive interface modulus and strength,propellant/liner adhesive interface modulus and strength on the location and degree of damage were discussed.The"dewetting"between the filled particles and matrix was the main damage when propellant cohesive failure occurred,and the critical strain threshold for this damage was about 30%.When the propellant/liner adhesive interface debonding occurred,the crack propagation path was consistent with the direction of the prefabricated crack.The damage forms of mixed failure included the filled-particles/matrix"dewetting",propel-lant/liner debonding and propellant matrix tearing.The critical strain for crack propagation at the propellant/liner adhesive in-terface was about 20%,and the critical strain for the"dewetting"and crack propagation was about 60%.The effects of propel-lant matrix strength,particle/matrix adhesive interface strength,and propellant/liner adhesive interface strength on the damage failure of the adhesive interface structure were more significant.As the first two parameters increased,the location of the"dewetting"moved towards to the propellant/liner adhesive interface.At the same time,the critical strength threshold for pro-pellant/liner adhesive interface that changed the damage failure mode of the adhesive interface structure was between 0.80 and 1.00 MPa.The damage mode and damage degree of the adhesive interface structure for NEPE propellant changes with the dif-ferent material parameters of the microstructure model.
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