Prediction of the cool-down time of a solid rocket motor by a surrogate model

Prediction of the cool-down time of a solid rocket motor is a significant requirement while constructing the viscoelastic structural model for the rocket propellant. This research is a part of an automated optimization framework to optimize a solid rocket propellant with slotted cross section. A surrogate model based on the response surface method is used to predict the cool-down time of the solid rocket propellant efficiently. Effects of the sectional geometric parameters on cool-down time of the system are investigated in detail and then by using the response surface method, the cool-down time of the solid rocket motor is formulated. Finally, response surface results are validated with the precise finite element solutions.