Effects of aluminum oxide particles and gas properties on the thermal response of solid rocket nozzle liners

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Volumn , Issue , 2008, Pages

  Hwang, Ki Young ^a,b   Yim, Yoo Jin ^a,b  

^a Agency for Defence Development   (South Korea)

^b 1st R and D Institute   (South Korea)

Author keywords

[No Author keywords available]

Indexed keywords

ALUMINUM AGGLOMERATION; ALUMINUM OXIDE PARTICLES; ALUMINUM POWDERS; ENERGETIC PLASTICIZER; GAS PROPERTIES; HTPB PROPELLANT; IN-LINE; LARGE PARTICLES; MECHANICAL EROSION; OXIDIZING SPECIES; SCANNING ELECTRON MICROSCOPE; THERMAL RESPONSE; THERMO-CHEMICAL; THROAT INSERT; VOLUMETRIC FRACTIONS;

AGGLOMERATION; ALUMINUM; EXHAUST GASES; EXPLOSIVES; OXIDES; PHOTOGRAPHY; PLASTICIZERS; PROPELLANTS; PROPULSION; ROCKET NOZZLES; ROCKETS; SCANNING ELECTRON MICROSCOPY; SOLVENTS; VEHICULAR TUNNELS;

HTPB PROPELLANTS;

EID: 77957847694     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (28)

1. Douglass, H. W., Collins Jr., J. H., Ellis, R. A., and Keller Jr., R. B., "Solid Rocket Motor Nozzles, Space Vehicle Design Criteria (Chemical Propulsion)," NASA SP-8115, 1975.
2. Hwang, K. Y. and Kang, Y. G., "Two-Dimensional Thermal Analysis for Carbonaceous Thermal Liner of Rocket Nozzle with Ablation and In-Depth Pyrolysis," Journal of the Korean Society of Propulsion Engineers, Vol. 3, No.2, 1999, pp. 37-47.
3. Ketner, D. M., and Hess, K. S., "Particle Impingement Erosion," AIAA Paper 79-1250, June 1979.
4. Devenas, A., "Development of Modern Solid Propellants," Journal of Propulsion and Power, Vol.19, No.6, 2003, pp. 1108-1128.
5. Sutton, G. P., Rocket Propulsion Elements, 6th ed., John Wiley & Sons, Inc., New York, 1992, pp. 416-455.
6. Shimada, T., Sekiguchi, M., and Sekino, N., "Flow Inside a Solid Rocket Motor with Relation to Nozzle Inlet Ablation," AIAA Journal, Vol.45, No.6, 2007, pp. 1324-1332.
7. Chaouat, B., "Flow Analysis of a Solid Propellant Rocket Motor with Aft Fins, "Journal of Propulsion and Power, Vol. 13, No. 2, 1997, pp. 194-196.
8. Morstadt, R. A., "A 3-D CFD Analysis of the Space Shuttle RSRM with Propellant Fins @ 1s Burn-back," AIAA Paper 2003-5105, July 2003.
9. Yim, Y. J., "The Tendency in Solid Propellant Technology for Missiles," Journal of the Korean Society of Propulsion Engineers, Vol.9, No.4, 2005, pp. 112-120.
10. Price, E. W., "Combustion of Metalized Propellants," in Fundamentals of Solid-Propellant Combustion (K.K. Kuo and M. Summerfield Eds.), Volume 90 of Progress in Astronautics and Aeronautics, AIAA, New York, 1984.
11. Srinivas, V. and Chakravarthy, S. R., "Computer Model of Aluminum Agglomeration on Burning Surface of Composite Solid Propellant, Journal of Propulsion and Power, Vol. 23, No. 4, 2007, pp. 728-736.
12. Sambamurthi, J. K., Price, E. W., and Sigman, R. K., "Aluminum Agglomeration in Solid-Propellant Combustion," AIAA Journal, Vol.22, No.8, 1984, pp. 1132-1138.
13. Cohen, N. S., "A Pocket Model for Aluminum Agglomeration in Composite Propellants," AIAA Journal, Vol.21, No.5, 1983, pp. 720-725.
14. Hermsen, R. W., "Aluminum Oxide Particle Size for Solid Rocket Motor Performance Prediction," Journal of Spacecraft and Rockets, Vol.18, No.6, 1981, pp. 483-490.
15. Johnston, W. A., Murdock, J. W., Koshigoe, S., and Than, P. T., "Slag Accumulation in the Titan Solid Rocket Motor Upgrade," Journal of Propulsion and Power, Vol. 11, No. 5, 1995, pp. 1012-1020.
16. Boraas, S., "Modeling Slag Deposition in the Space Shuttle Solid Rocket Motor," Journal of Spacecraft and Rockets, Vol.21, No.1, 1984, pp. 47-54.
17. th International Annual Conference of ICT, V27, Fraunhofer-Institut für Chemische Technologie, Pfinztal, Germany, 2004.
18. Dokhan, A., Price, E. W., Seitzman, J. M., and Sigman, R. K. "Combustion Mechanisms of Bimodal and Ultra-Fine Aluminum in AP Solid Propellant," AIAA Paper 2002-4173, July 2002.
19. Lengellé, G., Duterque, J., and Trubert, J. F., "Combustion of Solid Propellants," Internal Aerodynamics in Solid Rocket Propulsion, RTO-EN-023, published by NATO Research and Technology Organisation, Jan. 2004, [online database], URL: http://www.rta.nato.int/Pubs/RDP.asp?RDP=RTO-EN-023.
20. Hwang, C. J. and Chang, G. C., "Numerical Study of Gas-Particle Flow in a Solid Rocket Nozzle," AIAA Journal, Vol.26, No.6, 1988, pp. 682-689.
21. Klager, K., "The Interaction of the Efflux of Solid Propellants with Nozzle Materials," Propellants and Explosives, Vol.2, 1977, pp. 55-63.
22. Lapp, P. and Quesada, B., "Analysis of Solid Rocket Motor Nozzle," AIAA Paper 92-3616, June 1992.
23. Keswani, S. T., Andiroglu, E., Campbell, J. D., and Kuo, K.K., "Recession Behavior of Graphitic Nozzles in Simulated Rocket Motors," Journal of Spacecraft and Rockets, Vol.22, No.4, 1985, pp. 396-397.
24. Borie, V., Brulard, J., and Lengellé, G., "Aerothermochemical Analysis of Carbon-Carbon Nozzle Regression in Solid-Propellant Rocket Motors," Journal of Propulsion and Power, Vol.5, No.6, 1989, pp. 665-673.
25. Boyarintsev, V. I. and Zvyagin, Yu. V., "Turbulent Boundary Layer on Reacting Graphite Surface," Proceedings of the 5th International Heat Transfer Conference, FC6.8, Japan Society of Mechanical Engineers and Society of Chemical Engineers, Tokyo, Japan, Sep. 1974, pp. 264-268.
26. Bartz, D. R., "Turbulent Boundary-Layer Heat Transfer from Rapidly Accelerating Flow of Rocket Combustion Gases and of Heated Air" Advances in Heat Transfer, Vol. 2, edited by J. P. Hartnett and T. F. Irvine, Academic Press, New York, 1965.
27. Laturelle, F., Fiorot, S., and Wertheimer, T. B., "MSC. Marc-ATAS: Advanced Thermal Analysis Software for Modeling of Rocket Motors and Other Thermal Protection Systems," MSC Aerospace Conference, 2002, [online database], URL: http://www.mscsoftware.com/events/aero2002/partner/fullpaper. cfm?Start=41.
28. Potts, R. L., "Hybrid Integral/Quasi-Steady Solution of Charring Ablation," AIAA Paper 90-1677, June 1990.