A computational procedure for service-life estimation of a solid propellant rocket motor grain is developed. The propellant response is mathematically represented using a nonlinear damaging viscoelastic model. A finit...
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A computational procedure for service-life estimation of a solid propellant rocket motor grain is developed. The propellant response is mathematically represented using a nonlinear damaging viscoelastic model. A finite element analysis is then performed to identify potential failure modes of the grain and to determine the critical values of stress strain associated with the potential failure modes. Both the current and aged propellant samples are calibrated and the motor is analyzed Our the models representing the different ages of the motor. Based on the available strain capability and bond-line strength data, the grain service life is estimated to end by bond failure during cold firing.
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