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http://dx.doi.org/10.6108/KSPE.2018.22.1.036

Analysis of Boundary Layer in Solid Rocket Nozzle and Numerical Analysis of Thermal Response of Carbon/Phenolic using Finite Difference Method  

Seo, Sang Kyu (The 4th R&D Institute - 1st Directorate, Agency for Defense Development)
Hahm, Hee Cheol (The 4th R&D Institute - 1st Directorate, Agency for Defense Development)
Kang, Yoon Goo (The 4th R&D Institute - 1st Directorate, Agency for Defense Development)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.22, no.1, 2018 , pp. 36-44 More about this Journal
Abstract
The thermal response of carbon/phenolic used in a solid rocket nozzle liner was analyzed. In this paper, the numerical analysis of the thermal response of carbon/phenolic consists of (1) the integration equation of the boundary layer to obtain the convective heat transfer coefficient of the combustion gas on the rocket nozzle wall and (2) 1-D finite difference method for heat conduction of carbon/phenolic to calculate the ablation, char, and temperature. The calculated result was compared with the result of a blast-tube-type test motor. It is found that the calculated result shows good agreement with the thermal response of the test motor, except at the vicinity of the throat insert.
Keywords
Solid Rocket Nozzle; Integration Equation for Boundary Layer; Carbon/Phenolic Composite Material; Thermal Decomposition; Chemical Ablation;
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  • Reference
1 Davenas, A., Solid rocket propulsion technology, 1st ed., Pergamon Press, U.K., pp. 1-32, 1992.
2 Bartz, D.R., "Turbulent Boundary layer and heat transfer from rapidly accelerating flow of rocket combustion gases and of heated air", Advances in Heat Transfer, Vol. 2, pp. 1-108, 1965.
3 Ellis, R.A., "NASA Space Vehicle Design Criteria (Chemical Propulsion)-Solid Rocket Motor Nozzles," NASA SP-8115, 1975.
4 Shames, I.H., Mechanics of fluids, 4th ed., McGraw-Hill, N.Y., U.S.A., Ch. 10, 2003.
5 Levy, D., "Introduction to numerical analysis," Department of Mathematics and Center for Scientific Computation and Mathematical Modeling, University of Maryland, Baltimore, M.D., U.S.A., 2010.
6 Schlichting, H., Boundary-Layer Theory, 7th ed., McGraw Hill Inc., New York, N.Y., U.S.A., pp. 454, 1979.
7 Morkovin, M.V., Effects of Compressibility on Turbulent Flows, A. Favre ed., Gordon and Breach Inc., New York, N.Y., U.S.A., pp. 367- 380, 1964.
8 Bae, J.Y., Lee, Y.J., Bae, H.M., Ham, H.C. and Cho, H.H., "Conjugate simulation of rocket nozzle with 1-D algebraic thermal decomposition equation," 2015 KSPE Fall Conference, Jeju, Korea, pp. 145-148, Nov. 2015.
9 Kumar, R.R., Vinod, G., Renjith, S., Rajeev, G., Jana, M.K. and Harikrishnan, R., "Thermostructural analysis of composite structures," Materials Science and Engineering: A, Vol. 412, No. 1, pp. 66-70, 2005.   DOI
10 Lapp, P. and Quesada, B., "Analysis of solid rocket motor nozzle," 28th Joint Propulsion Conference and Exhibit, Nashville, T.N., U.S.A, AIAA 92-3616, Jul. 1992.
11 Boyarintsev, V.I. and Zvyagin, Yu. V., "Turbulent Boundary Layer on Reacting Graphite Surface," 5th Int. Heat Transfer Conference, Tokyo, Japan, pp. 264-268, Sep. 1974.
12 Hwang, K.Y., Yim, Y.J., Ham, H.C., Kang, Y.G. and Bae, J.C., "Effects of Solid Propellant Gases on the Thermal Response of Nozzle Liner," Journal of the Korean Society of Propulsion Engineers, Vol. 11, No. 2, pp. 26-36, 2007.
13 Hwang, K.Y. and Kang, Y.G., "Two-dimensional Thermal Analysis for Carbonacious Thermal Liner of Rocket Nozzle with Ablation and In-depth Pyrolysis," Journal of the Korean Society of Propulsion Engineers, Vol. 3, No. 2, pp. 37-47, 1999.
14 Kim, Y.C., "Thermal Decomposition and Ablation Analysis of Solid Rocket Propulsion," Journal of the Korean Society of Propulsion Engineers, Vol. 14, No. 5, pp. 32-44, 2010.
15 McBride, B.J. and Gordon, S., "Computer Program for Calculation of Complex Chemical Equilibrium Composition and Applications, II. Users Manual and Program Description," NASA RP-1311, 1996.