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 |
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Title of host publication | 47th AIAA Thermophysics Conference, 2017 |
Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
ISBN (Print) | 9781624104992 |
DOIs | |
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 |
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Conference
Conference | 47th AIAA Thermophysics Conference, 2017 |
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Country/Territory | United States |
City | Denver |
Period | 5/06/17 → 9/06/17 |
Bibliographical note
Publisher Copyright:© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.