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

Ceyhun Tola; Melike Nikbay

doi:10.2514/6.2017-4345

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

Ceyhun Tola
, Melike Nikbay

Department of Astronautical Engineering

Istanbul Technical University

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-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 language	English
Title of host publication	47th AIAA Thermophysics Conference, 2017
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)	9781624104992
DOIs	https://doi.org/10.2514/6.2017-4345
Publication status	Published - 2017
Event	47th AIAA Thermophysics Conference, 2017 - Denver, United States Duration: 5 Jun 2017 → 9 Jun 2017

Publication series

Name	47th AIAA Thermophysics Conference, 2017

Conference

Conference	47th AIAA Thermophysics Conference, 2017
Country/Territory	United States
City	Denver
Period	5/06/17 → 9/06/17

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

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10.2514/6.2017-4345

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title = "Prediction of the cool-down time of a solid rocket motor by a surrogate model",

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.",

author = "Ceyhun Tola and Melike Nikbay",

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N2 - 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.

AB - 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.

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DO - 10.2514/6.2017-4345

M3 - Conference contribution

AN - SCOPUS:85086689552

SN - 9781624104992

T3 - 47th AIAA Thermophysics Conference, 2017

BT - 47th AIAA Thermophysics Conference, 2017

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

T2 - 47th AIAA Thermophysics Conference, 2017

Y2 - 5 June 2017 through 9 June 2017

ER -

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

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