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Journal of Heat Transfer | Volume 127 | Issue 9 | Technical Brief
TECHNICAL BRIEFS

New Method to Determine the Velocities of Particles on a Solid Propellant Surface in a Solid Rocket Motor

[+] Author and Article Information
Yumin Xiao

Mechanical Engineering Department,  University of Wisconsin-Milwaukee, Milwaukee, WI 53211

R. S. Amano

Mechanical Engineering Department,  University of Wisconsin-Milwaukee, Milwaukee, WI 53211amano@uwm.edu

Timin Cai, Jiang Li

College of Astronautics,  Northwestern Polytechnical University, Xi’an, Shaanxi Province, 710072 People’s Republic of China

J. Heat Transfer 127(9), 1057-1061 (Apr 19, 2005) (5 pages) doi:10.1115/1.1999652 History: Received March 05, 2003; Revised April 19, 2005
Article
References
Figures
Tables
Citing Articles

Use of aluminized composite solid propellants and submerged nozzles are common in solid rocket motors (SRM). Due to the generation of slag, which injects into a combusted gas flow, a two-phase flow pattern is one of the main flow characteristics that need to be investigated in SRM. Validation of two-phase flow modeling in a solid rocket motor combustion chamber is the focus of this research. The particles’ boundary conditions constrain their trajectories, which affect both the two-phase flow calculations, and the evaluation of the slag accumulation. A harsh operation environment in the SRM with high temperatures and high pressure makes the measurement of the internal flow field quite difficult. The open literature includes only a few sets of experimental data that can be used to validate theoretical analyses and numerical calculations for the two-phase flow in a SRM. Therefore, mathematical models that calculate the trajectories of particles may reach different conclusions mainly because of the boundary conditions. A new method to determine the particle velocities on the solid propellant surface is developed in this study, which is based on the x-ray real-time radiography (RTR) technique, and is coupled with the two-phase flow numerical simulation. Other methods imitate the particle ejection from the propellant surface. The RTR high-speed motion analyzer measures the trajectory of the metal particles in a combustion chamber. An image processing software was developed for tracing a slug particle path with the RTR images in the combustion chamber, by which the trajectories of particles were successfully obtained.
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Copyright © 2005 by American Society of Mechanical Engineers
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References

1
Salita, M., 1995, “Deficiencies and Requirements in Modeling of Slag Generation in Solid Rocket Motors,” J. Propul. Power, 11  (1), pp. 10–23.
2
Boraas, S., 1984, “Modeling Slag Deposition in the Space Shuttle Solid Rocket Motor,” J. Spacecr. Rockets, 21  (1), pp. 47–54.
3
Haloulakos, V. E., 1991, “Slag Mass Accumulation in Spinning Solid Rocket Motors,” J. Propul. Power, 7  (1), pp. 14–21.
4
Hess, E., Chen, K., Acosta, P., Brent, D., and Fendell, F., 1992, “Effect of Aluminized-Grain Design on Slag Accumulation,” J. Spacecr. Rockets, 29  (5), pp. 697–703.
5
Meyer, R. X., 1992, “In-Flight Formation of Slag in Spinning Solid Propellant Rocket Motors,” J. Propul. Power, 8  (1), pp. 45–50.
6
Golafshani, M., and Loh, H.-T., 1989, “Computation of Two-Phase Viscous Flow in Solid Rocket Motor Using a Flux-Split Eulerian–Lagrangian Technique,” AIAA Report No. 89-2785.
7
Salita, M., Smith-Kent, R., Golafshani, M. T., Abel, R., and Pratt, D., 1990, “Prediction of Slag Accumulation in SICBM Static Flight Motors,” Thiokol TWR-10259.
8
Sabnis, J. S., De Jong, F. J., and Gibeling, H. J., 1992, “Calculation of Particle Trajectories in Solid Rocket Motors With Arbitrary Acceleration,” J. Propul. Power, 8  (5), pp. 961–967.
9
Chang, I. S., 1991, “An Efficient Intelligent Solution for Viscous Flows Inside Solid Rocket Motors,” AIAA Report No. 91-2429.
10
Chauvot, J. F., Dumas, L., and Schmeisser, K., 1995, “Modeling of Alumina Slag Formation in Solid Rocket Motors,” AIAA Report No. 95-2729.
11
Liaw, P., Shang, H. M., and Shih, M. H., 1995, “Numerical Investigation of Slag Behavior With Combustion/Evaporation/Breakup/VOF Models for Solid Rocket Motors,” AIAA Report No. 95-2726.
12
Braithwaite, P. C., Christensen, W. N., and Daugherty, V., 1988, “Quench Bomb Investigation of Aluminum Oxide Formation From Solid Rocket Propellants (Part I): Experimental Methodology,” "Proceedings of the 25th JANNAF Combustion Meeting", Vol. 1 , pp. 178–184.
13
Char, J. M., Kou, K. K., and Hsieh, K. C., 1987, “Observation of Breakup Process of Liquid Jets Using Real-Time X-Ray Radiography,” AIAA Report No. 87-2137.
14
Wen, C. Y., and Yu, Y. H., 1966, “Mechanics of Fluidization,” Chem. Eng. Prog., Symp. Ser., 62 , pp. 100–111.

Figures

Grahic Jump Location
+Layout of the real-time x-ray radiography system
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Layout of the real-time x-ray radiography system
Figure 1

Layout of the real-time x-ray radiography system

Grahic Jump Location
+Layout of x-ray imaging
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Layout of x-ray imaging
Figure 2

Layout of x-ray imaging

Grahic Jump Location
+Layout of test rig
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Layout of test rig
Figure 3

Layout of test rig

Grahic Jump Location
+Layout of propellant model
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Layout of propellant model
Figure 4

Layout of propellant model

Grahic Jump Location
+Initial RTR image
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Initial RTR image
Figure 5

Initial RTR image

Grahic Jump Location
+Final RTR image after processing
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Final RTR image after processing
Figure 6

Final RTR image after processing

Grahic Jump Location
+Calculated trajectory with different ejection velocity
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Calculated trajectory with different ejection velocity
Figure 7

Calculated trajectory with different ejection velocity

Grahic Jump Location
+Comparison between calculated trajectory and measured trajectory
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Comparison between calculated trajectory and measured trajectory
Figure 8

Comparison between calculated trajectory and measured trajectory

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