The Analysis of Stress Strain from Voids in Solid Propellant by using Finite Element Method
Article Sidebar
Main Article Content
Abstract
One problem encountered in the casting of rocket propellants is the problem of voids in the propellant which affects load in the propellant from the use of rockets in various conditions. The success of a rocket depends on many factors. One thing is the strength of the propellant. The strength of propellant was estimated by constructing the master curve which obtained from the results of the tensile test of propellant samples. In this research, stress strain analysis in propellant containing voids is performed by using the finite element method. The result of analysis in case of high temperature at 60 degree Celsius the maximum stress from voids. It was found that the strain was below the maximum value. That is, the effect of temperature and voids did not damage the propellant. In the case of the pressure inside motor, the strain of the propellant remains at an acceptable level. The case of an acceleration of 70 g, the stress below the maximum value which safety factor 1.3, that is from three cases, the acceleration of the rocket rather affects the propellant. However, even though there is a problem with voids, the propellant can still hold the loads of working of rocket.
Downloads
Article Details
This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.
Journal of TCI is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International (CC BY-NC-ND 4.0) licence, unless otherwise stated. Please read our Policies page for more information...
References
W. M. Adel and L. Guo - Zhu, “Analysis of Mechanical Properties for AP/HTPB Solid Propellant under Different Loading Conditions,” Int. J. Aerosp. Mech. Eng., vol. 11, no. 12, pp. 1915 - 1919, 2017.
W. M. Adel and L. Guo - Zhu, “Different Method for Developing Relaxation Modulus Master Curves of AP-HTPB Solid Propellant,” Chin. J. Energ. Mater., vol. 25, no. 10, pp. 810 - 816, 2017.
S. W. Chyuan, “Nonlinear Thermoviscoelastic Analysis of Solid Propellant Grains Subject to Temperature Loading,” Finite Elem. Anal. Des., vol. 38, no. 7, pp. 613 - 630, 2002.
S. W. Chyuan, “Studies of Poisson’s Ratio Variation for Solid Propellant Grains Under Ignition Pressure Loading,” Int. J. Press. Vessel. Pip., vol. 80, no. 12, pp. 871 - 877, 2003.
Z. J. Wang, H. F. Qiang, G. Wang, and B. Geng, “Strength Criterion of Composite Solid Propellants Under Dynamic Loading,” Def. Technol., vol. 14, no. 5, pp. 457 - 462, 2018.
B. K. Bihari, V. S. Wani, N. P. N. Rao, P. P. Singh, and B. Bhattacharya, “Determination of Activation Energy of Relaxation Events in Composite Solid Propellants by Dynamics Mechanical Analysis,” Def. Sci. J., vol. 64, no. 2, pp. 173 - 178, 2014.
A. Davenas, Solid Rocket Propulsion Technology. New York, NY, USA: Pergamon Press, 1989.
M. L. Williams, R. F. Landel, and J. D. Ferry, “The Temperature Dependence of Relaxation Mechanisms in Amorphous Polymers and Other Glass-forming Liquids,” J. Am. Chem. Soc., vol. 77, no. 14, pp. 3701 - 3707, 1955.