A simplified finite element method for failure analysis in adhesive-bonded nozzle diffuser of solid rocket motors

Abstract The adhesive bond between the nozzle diffuser shell and insulation layer of solid rocket motors (SRM) is widely used due to its lightweight, simple design, easy operation. mechanism adhesive-bonded failure them a concern for designers. In this paper, simplified finite element method analysis in SRM proposed. method, shell, layer, are considered elastic. maximum Von Mises stress criterion assumed be suitable adhesive. simulated by using user subroutine VUSDFLD commercial Finite Element Analysis software ABAQUS. verified but effective based on comparison with experimental results. process under external load can well simulated, critical accurately predicted. addition, utilized study several kinds original debonding. It suggested that axial debonding ratio should less than 60%, circumferential angle smaller 30° conical section diffuser.