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

Ceyhun Tola, Melike Nikbay

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

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.

Original languageEnglish
Title of host publication47th AIAA Thermophysics Conference, 2017
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104992
DOIs
Publication statusPublished - 2017
Event47th AIAA Thermophysics Conference, 2017 - Denver, United States
Duration: 5 Jun 20179 Jun 2017

Publication series

Name47th AIAA Thermophysics Conference, 2017

Conference

Conference47th AIAA Thermophysics Conference, 2017
Country/TerritoryUnited States
CityDenver
Period5/06/179/06/17

Bibliographical note

Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

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