Structural Behavior Examination of Frequently Used Solid Propellant Sections Under Centrifugal Loading Using Response Surface Method

Keywords: Solid Rocket Motor, Centrifugal Loading, Finite Element Analysis, Viscoelasticity, Response Surface Method

Abstract

This research aims to examine structural responses of frequently used solid propellant sections such as tubular, star, slotted, wagon wheel, and anchor subjected to centrifugal acceleration load. Viscoelastic finite element models of the grains having different dimensions are constructed and solved in Abaqus environment using in house parametric Python scripts prepared within the content of this work. Validation of the finite element models is accomplished comparing finite element results with an analytical equation found from literature. Finally, different response surfaces are constructed in Minitab environment to determine effect of grain cross-section parameters on von Mises stress level of the propellant. Thus, the most effective cross-section parameters on von Mises stress are determined for the examined grain shapes.

Author Biographies

Ceyhun Tola, Aselsan Inc.

Ceyhun TOLA received his B.Sc. degrees in Aeronautical and Astronautical Engineering Departments from Faculty of Aeronautics and Astronautics, Istanbul Technical University (ITU) under the double major program in 2010. He received his M.Sc. and Ph.D. degrees in Aeronautical and Astronautical Engineering from Institute of Science and Technology, ITU in 2012 and 2017 sequentially. During the M.Sc, he worked as graduate research assistant in ITU Trisonic Lab. During the Ph.D, he worked for Roketsan Missiles Inc., Vestel Defense Industry, and Sun Express Airlines as engineer in between 2011-2016. He worked as assistant professor at Astronautical Engineering Department of University of Turkish Aeronautical Association between 2018-2020. Currently, he has been working for Aselsan Inc. as senior expert engineer since August 2020. His research interests are solid rocket motor design, finite element method, response surface method, aeroelasticity, and design optimization.

Hatice Begüm Eylenoğlu, University of Turkish Aeronautical Association

Hatice Begüm EYLENOĞLU received her B.Sc. degree in Astronautical Engineering from Faculty of Aeronautics and Astronautics, University of Turkish Aeronautical Association, Turkey in 2020. Her research interests are finite element analysis, structural analysis of solid rocket motors, quadrotor design, and remote operating vehicle design.

References

[1] Z. Shen, L. Zhang, and Y. Li, "Structural integrity analysis and experimental investigation for solid rocket motor grain subjected to low temperature ignition," in 7th Asian Conference on Mechanical and Materials Engineering, MATEC 2019, Tokyo, Japan, June 14-17, 2019, Vol. 293, No. 4005.
[2] N. Gligorijević, S. Antonović, S. Živković, B. Pavković, and V. Rodić, "Thermal and acceleration load analysis of new 122 mm rocket," Scientific Technical Review, vol. 66, no. 3, pp. 3-11, December 2016.
[3] K. Qui, and X. Zhang, "Finite element analysis of propellant of solid rocket motor during ship motion," Propulsion and Power Research, vol. 2, no. 1, pp. 50-55, March 2013.
[4] H. Chu, and J. Chou, "Effect of cooling load on the safety factor of propellant grains," Journal of Propulsion and Power, vol. 29, no. 1, pp. 27-33, January 2013.
[5] W. M. Adel, and L. Guozhu, "Study of Cooldown Thermal Loading Effect on the Bore Deformation of Viscoelastic Solid Propellant Grain," in AIAA Propulsion and Energy Forum, Atlanta, GA, USA, July 10-12, 2017.
[6] M. Kurian, K. Renganathan, and S. M. Sobichen, "Structural analysis of viscoelastic solid propellant grain," International Journal of Scientific & Engineering Research, vol. 7, no. 10, pp. 117-122, October 2016.
[7] B. Tunç, Ş. Özüpek, E. Podnos, and U. Arkun, "Thermal Cyclic Stress Analysis of a Solid Rocket Motor," Journal of Spacecraft and Rockets, vol. 56, no. 1, pp. 179-189, August 2018.
[8] J. D. Mattingly, Elements of Propulsion: Gas Turbines and Rockets. American Institute of Aeronautics and Astronautics, Virginia, 2006, pp. 218.
[9] NASA SP-8076, Solid Propellant Grain Design and Internal Ballistics, 1972.
[10] C. Tola, and M. Nikbay, "Solid rocket motor propellant optimization with coupled internal ballistic–structural interaction approach," Journal of Spacecraft and Rockets, vol. 55, no. 4, pp. 936-947, April 2018.
[11] C. Tola, and M. Nikbay, "Internal ballistic modeling of a solid rocket motor by analytical burnback analysis," Journal of Spacecraft and Rockets, vol. 56, no. 2, pp. 498-516, March 2019.
[12] AGARD AR-350, Structural Assessment of Solid Propellant Grains, 1997.
[13] NASA SP-8073, Solid Propellant Grain Structural Analysis, 1973.
Published
2021-07-30
How to Cite
[1]
C. Tola and H. Eylenoğlu, “Structural Behavior Examination of Frequently Used Solid Propellant Sections Under Centrifugal Loading Using Response Surface Method”, JAST, vol. 14, no. 2, pp. 231-242, Jul. 2021.
Section
Articles