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Numerical Investigation of a N2O/HTPB Hybrid Rocket Motor with a Dual-Vortical-Flow (DVF) Design

Published online by Cambridge University Press:  24 January 2017

A. Lai ,
Y. C. Lin ,
S. S. Wei ,
T. H. Chou ,
J. W. Lin ,
J. S. Wu  and
Y. S. Chen
A. Lai
Affiliation:
Department of Mechanical EngineeringNational Chiao Tung UniversityHsinchu, Taiwan
Y. C. Lin
Affiliation:
Taiwan Innovative Space, Inc.Miaoli, Taiwan
S. S. Wei
Affiliation:
Taiwan Innovative Space, Inc.Miaoli, Taiwan
T. H. Chou
Affiliation:
Taiwan Innovative Space, Inc.Miaoli, Taiwan
J. W. Lin
Affiliation:
Department of Mechanical EngineeringNational Chiao Tung UniversityHsinchu, Taiwan
J. S. Wu*
Affiliation:
Department of Mechanical EngineeringNational Chiao Tung UniversityHsinchu, Taiwan
Y. S. Chen
Affiliation:
National Space OrganizationNational Applied Research LaboratoriesHsinchu, Taiwan
*
*Corresponding author (chongsin@faculty.nctu.edu.tw)
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Abstract

A compact hybrid rocket motor design that incorporates a dual-vortical-flow (DVF) concept is proposed. The oxidizer (nitrous oxide, N2O) is injected circumferentially into various sections of the rocket motor, which are sectored by several solid fuel “rings” (made of hydroxyl-terminated polybutadiene, HTPB) that are installed along the central axis of the motor. The proposed configuration not only increases the residence time of the oxidizer flow, it also implies an inherent “roll control” capability of the motor. Based on a DVF motor geometry with a designed thrust level of 11.6 kN, the characteristics of the turbulent reacting flow within the motor and its rocket performance were analyzed with a comprehensive numerical model that implements both real-fluid properties and finite-rate chemistry. Data indicate that the vacuum specific impulse (Isp) of the DVF motor could reach 278 s. The result from a preliminary ground test of a lab-scale DVF hybrid rocket motor (with a designed thrust level of 3,000 N) also shows promising performance. The proposed DVF concept is expected to partly resolve the issue of scalability, which remains challenging for hybrid rocket motors development.

Keywords

Hybrid rocket motorComputational fluid dynamicsDual-vortical-flow designN2O/HTPB
Type
Research Article
Information
Journal of Mechanics , Volume 33 , Issue 6 , December 2017 , pp. 853 - 862
Copyright
Copyright © The Society of Theoretical and Applied Mechanics 2017 

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References

1. Sutton, G. P. and Biblarz, O., Rocket Propulsion Elements, 7th Edition, John Wiley & Sons, Inc., NY, U.S.A. (2001).Google Scholar
2. Kuo, K. K. and Chiaverini, M. J., Fundamentals of Hybrid Rocket Combustion and Propulsion, American Institute of Aeronautics and Astronautics, Reston, VA, U.S.A. (2007).CrossRefGoogle Scholar
3. Flittie, K. J., Estey, P. N. and Kniffen, R. J., “The Aquila Launch Vehicle,” Acta Astronautica, 28, pp. 99–110 (1992).CrossRefGoogle Scholar
4. Jenkins, R. and Cook, J., “A Preliminary Analysis of Low Frequency Pressure Oscillations in Hybrid Rocket Motors,” 31st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, U.S.A. (1995).Google Scholar
5. Park, K.-S. and Lee, C., “Low Frequency Instability in Laboratory-scale Hybrid Rocket Motors,” Aerospace Science and Technology, 42, pp. 148–157 (2015).Google Scholar
6. Marxman, G. and Gilbert, M., “Turbulent Boundary Layer Combustion in the Hybrid Rocket,” Symposium (International) on Combustion, 9, pp. 371–383 (1963).Google Scholar
7. Carmicino, C., Scaramuzzino, F. and Russo Sorge, A., “Trade-off Between Paraffin-based and Aluminium-loaded HTPB Fuels to Improve Performance of Hybrid Rocket Fed with N2O,” Aerospace Science and Technology, 37, pp. 81–92 (2014).Google Scholar
8. Kim, S. et al., “Regression Characteristics of the Cylindrical Multiport Grain in Hybrid Rockets,” Journal of Propulsion and Power, 29, pp. 573–581 (2013).Google Scholar
9. Lee, T. and Tsai, H., “Fuel Regression Rate in a Paraffin-HTPB Nitrous Oxide Hybrid Rocket,” 7th Asia-Pacific Conference on Combustion, Taiwan (2009).Google Scholar
10. Cantwell, B., Karabeyoglu, A. and Altman, D., “Recent Advances in Hybrid Propulsion,” International Journal of Energetic Materials and Chemical Propulsion, 9, pp. 305–326 (2010).Google Scholar
11. Chandler, A., Jens, E., Cantwell, B. and Hubbard, G. S., “Visualization of the Liquid Layer Combustion of Paraffin Fuel for Hybrid Rocket Applications,” 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, U.S.A. (2012).Google Scholar
12. Sun, X., Tian, H., Yu, N. and Cai, G., “Regression Rate and Combustion Performance Investigation of Aluminum Metallized HTPB/98HP Hybrid Rocket Motor with Numerical Simulation,” Aerospace Science and Technology, 42, pp. 287–296 (2015).Google Scholar
13. Haag, G. S., “Alternative Geometry Hybrid Rockets for Spacecraft Orbit Transfer,” Ph.D. Dissertation, School of Electronic Engineering, Information Technology and Mathematics, University of Surrey, Surrey, United Kingdom (2001).Google Scholar
14. Nagata, H. et al., “Development of CAMUI Hybrid Rocket to Create a Market for Small Rocket Experiments,” Acta Astronautica, 59, pp. 253–258 (2006).Google Scholar
15. Lazzarin, M. et al., “CFD Simulation of a Hybrid Rocket Motor with Liquid Injection,” 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, U.S.A. (2011).Google Scholar
16. Chen, Y., Chou, T.-H., Lai, A. and Wu, J.-S., “N2O-HTPB Hybrid Rocket Combustion Modeling with Mixing Enhancement Designs,” 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, U.S.A. (2013).Google Scholar
17. Kumar, C. P. and Kumar, A., “Effect of Swirl on the Regression Rate in Hybrid Rocket Motors,” Aerospace Science and Technology, 29, pp. 92–99 (2013).Google Scholar
18. Chou, T.-H., “Numerical and Experimental Investigation of Single-Port Hybrid Rocket Propulsion System with Nitrous Oxide and Hydroxyl-terminated Polybutadiene (HTPB) using Mixing Enhancer(s),” Ph.D. Dissertation, Department of Mechanical Engineering, National Chiao Tung University, Hsinchu, Taiwan (2015).Google Scholar
19. Li, C., Cai, G. and Tian, H., “Numerical Analysis of Combustion Characteristics of Hybrid Rocket Motor with Multi-section Swirl Injection,” Acta Astronautica, 123, pp. 26–36 (2016).Google Scholar
20. Karabeyoglu, M. A., “Nitrous Oxide and Oxygen Mixtures (Nytrox) as Oxidizers for Rocket Propulsion Applications,” Journal of Propulsion and Power, 30, pp. 696–706 (2014).Google Scholar
21. Dayal Swami, R. and Gany, A., “Analysis and Testing of Similarity and Scale Effects in Hybrid Rocket Motors,” Acta Astronautica, 52, pp. 619–628 (2003).Google Scholar
22. Chelaru, T.-V. and Mingireanu, F., “Hybrid Rocket Engine, Theoretical Model and Experiment,” Acta Astronautica, 68, pp. 1891–1902 (2011).CrossRefGoogle Scholar
23. Shan, F., Hou, L. and Piao, Y., “Combustion Performance and Scale Effect from N2O/HTPB Hybrid Rocket Motor Simulations,” Acta Astronautica, 85, pp. 1–11 (2013).Google Scholar
24. Chen, Y.-S. et al., “Dual-Vortical-Flow Hybrid Rocket Engine,” US Patent Number US 9458796 B2 (2014).Google Scholar
25. Chen, Y.-S. et al., “Multiphysics Simulations of Rocket Engine Combustion,” Computers & Fluids, 45, pp. 29–36 (2011).Google Scholar
26. Lai, G., Chou, T., Wu, J. and Chen, Y., “Numerical and Experimental Investigation of a Compact Hybrid Rocket Engine,” Twelfth International Conference on Flow Dynamics, Japan (2015).Google Scholar
27. Zhang, S., Liu, J. and Zhao, X., “An Integrated CFD Tool for Lunch Vehicles Base-Heating Analyses,” 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, U.S.A. (2006).Google Scholar
28. Chen, Y. S. and Kim, S. W., “Computation of Turbulent Flows Using an Extended k-epsilon Turbulence Closure Model,” NASA CR-179204, NASA Marshall Space Flight Center, Huntsville, AL, U.S.A. (1987).Google Scholar
29. Chen, Y., Cheng, G. and Farmer, R., “Reacting and Non-reacting Flow Simulation for Film Cooling in 2-D Supersonic Flows,” AIAA/SAE/ASME/ASEE 28th Joint Propulsion Conference and Exhibit, U.S.A. (1992).Google Scholar
30. Smith, G. P. et al., “GRI-Mech 3.0,” http://www.me.berkeley.edu/gri_mech/.Google Scholar
31. Brokaw, R. S., “Ignition Kinetics of the Carbon monoxide-Oxygen Reaction,” Symposium (International) on Combustion, 11, pp. 1063–1073 (1967).Google Scholar
32. Edelman, R. and Economos, C., “A Mathematical Model for Jet Engine Combustor Pollutant Emissions,” AIAA/SAE 7th Propulsion Joint Specialist Conference, U.S.A. (1971).Google Scholar
33. Olson, D. B. and Gardiner, W. C., “Combustion of Methane in Fuel-rich Mixtures,” Combustion and Flame, 32, pp. 151–161 (1978).Google Scholar
34. Annon, P., Spray Combustion of Synthetic Fuels. Phase II: Spray-combustion phenomena, DOE/PC/40276-5, Science Applications, Inc., Chatsworth, CA, U.S.A. (1983).Google Scholar
35. Warnatz, J., “Rate Coefficients in the C/H/O System,” Combustion Chemistry, Springer US, NY, U.S.A., pp. 197–360 (1984).Google Scholar
36. Chen, Y. S., Shang, H. M. and Liaw, P., “A Fast Algorithm for Transient All-Speed Flows and Finite-Rate Chemistry,” AIAA Space Programs and Technologies Conference, U.S.A. (1996).Google Scholar
37. McBride, B. J., Zehe, M. J. and Gordon, S., “NASA Glenn Coefficients for Calculating Thermodynamic Properties of Individual Species,” NASA/TP-2002-211556, NASA Glenn Research Center, Cleveland, OH, U.S.A. (2002).Google Scholar
38. Lai, G. et al., “Numerical and Experimental Investigation of HDPE Hybrid Propulsion with Dual Vortical-Flow Chamber Designs,” 51st AIAA/SAE/ASEE Joint Propulsion Conference, U.S.A. (2015).Google Scholar