OJFD  Vol.3 No.2 A , July 2013
A Study of Thermal Response and Flow Field Coupling Simulation around Hayabusa Capsule Loaded with Light-Weight Ablator
ABSTRACT

The numerical simulation of flow field around Hayabusa capsule loaded with light-weight ablator thermal response coupled with pyrolysis gas flow inside the ablator was carried out. In addition, the radiation from high temperature gas around the capsule was coupled with flow field. Hayabusa capsule reentered the atmosphere about 12 km/sec in velocity and Mach number about 30. During such an atmospheric entry, space vehicle is exposed to very savior aerodynamic heating due to convection and radiation. In this study, Hayabusa capsule was treated as a typical model of the atmospheric entry spacecraft. The light-weight ablator had porous structure, and permeability was an important parameter to analyze flow inside ablator. In this study, permeability was a variable parameter dependent on density of ablator. It is found that the effect of permeability of light-weight ablator was important with this analysis.


Cite this paper
H. Kihara, N. Hirata and K. Abe, "A Study of Thermal Response and Flow Field Coupling Simulation around Hayabusa Capsule Loaded with Light-Weight Ablator," Open Journal of Fluid Dynamics, Vol. 3 No. 2, 2013, pp. 100-107. doi: 10.4236/ojfd.2013.32A016.
References
[1]   T. Yamada, N. Ishii, Y. Inatani and M. Honda, “Thermal Protection System of the Reentry Capsule with Superorbital Velocity,” Institute of Space and Astronautical Science Report Source Publishing No. 17, 2003, pp. 245-261.

[2]   M. A. Covington, J. M. Heinemann, H. E. Goldstein, Y.-K. Chen, I. Terrazas-Salinas, J. A. Balboni, J. Olejniczak and E. R. Martinez, “Performance of a Low Density Ablative Heatshield Material,” Journal of Spacecraft and Rockets, Vol. 45, No. 4, 2008, pp. 854-864.

[3]   T. Yamada, Y. Ishida, T. Suzuki, K. Takasaki, K. Fujita, T. Ogasawara and T. Abe, “Development of High and Low Density Ablators for Dash-II and Future Reentry Missions,” Proceedings of the 27th International Symposium on Space Technology and Science, Tsukuba, 5-12 July 2009, p. e-03.

[4]   Y. K. Chen and F. S. Milos, “Ablation and Thermal Response Program for Spacecraft Heatshield Analysis,” Journal of Spacecraft and Rockets, Vol. 36, No. 3, 1999, pp. 475-483.

[5]   Y. K. Chen and F. S. Milos, “Two-Dimensional Implicit Thermal Response and Ablation Program for Charring Materials,” Journal of Spacecraft and Rockets, Vol. 38, No. 4, 2001, pp. 473-481.

[6]   H. Ahn, C. Park and K. Sawada, “Response of Heatshield Material at Stagnation Point of Pioneer-Venus Probes,” Journal of Thermophysics and Heat Transfer, Vol. 16, No. 3, 2002, pp. 432-439.

[7]   T. Suzuki, K. Sawada, T. Yamada and Y. Inatani, “Thermal Response of Ablative Test Piece in Arc-Heated Wind Tunnel,” AIAA Paper No. 2004-0341, 2004.

[8]   T. Suzuki, T. Sakai and T. Yamada, “Calculation of Thermal Response of Ablator under Arcjet Flow Condition,” Journal of Thermophysics and Heat Transfer, Vol. 21, No. 2, 2007, pp. 257-266.

[9]   S. Nozawa, T. Kanazaka, H. Kihara and K. Abe, “Experimental and Numerical Studies of Spallation Particles Ejected from A Light-Weight Ablator,” Proceedings of 61st International Astronautical Congress, Prague, 27 September-1 October 2010, IAC-10-C2.7.7.

[10]   Y. Takahashi, H. Kihara and K. Abe, “Effect of Radiative Heat Transfer in Arc-Heated Nonequilibrium Flow Simulation,” Journal of Physics D: Applied Physics, Vol. 43, 2010, Article ID: 185201. doi:10.1088/0022-3727/43/18/185201

[11]   N. Hirata, S. Nozawa, Y. Takahashi, H. Kihara and K. Abe, “Numerical Study of Pyrolysis Gas Flow and Heat Transfer inside an Ablator,” Computational Thermal Sciences, Vol. 4, No. 3, 2012, pp. 225-242.

[12]   C. Park, R. L. Jaffe and H. Partridge, “Chemical-Kinetic Parameters of Hyperbolic Earth Entry,” Journal of Thermophysics and Heat Transfer, Vol. 15, No. 1, 2001, pp. 76-90.

[13]   C. Park, “Rotational Relaxation of N2 behind a Strong Shock Wave,” Journal of Thermophysics and Heat Transfer, Vol. 18, No. 4, 2004, pp. 527-533. doi:10.2514/1.11442

[14]   C. Park, “Problems of Rate Chemistry in the Flight Regimes of Aeroassisted Orbital Transfer Vehicles,” AIAA Paper 84-1730, 1985.

[15]   J. P. Appleton and K. N. C. Bray, “The Conservation Equations for a Nonequilibrium Plasma,” Journal of Fluid Mechanics, Vol. 20, No. 4, 1964, pp. 659-672.

[16]   P. A. Gnoffo, R. N. Gupta and J. L. Shinn, “Conservation Equations and Physical Models for Hypersonic Air Flows in Thermal and Chemical Nonequilibrium,” National Aeronautics and Space Administration, Washington DC, 1989.

[17]   S. S. Lazdinis and S. L. Petrie, “Free Electron and Vibrational Temperature Nonequilibrium in High Temperature Nitrogen,” Physics of Fluids, Vol. 17, No. 8, 1974, pp. 1539-1546.

[18]   J.-H. Lee, “Electron-Impact Vibrational Relaxation in High-Temperature Nitrogen,” Journal of Thermophysics and Heat Transfer, Vol. 7, No. 3, 1993, pp. 399-405.

[19]   T. Sakai, “Computational Simulation of High-Enthalpy Arc Heater Flows,” Journal of Thermophysics and Heat Transfer, Vol. 21, No. 1, 2007, pp. 77-85.

[20]   M. Yamada, Y. Matsuda, H. Hirata, Y. Takahashi, H. Kihara and K. Abe, “Numerical Simulation of Flow Field and Heat Transfer around HAYABUSA Reentry Capsule,” Proceedings of the 28th International Symposium on Space Technology and Science, Okinawa, 5-12 June 2011, p. e-38.

[21]   Y. K. Chen and F. S. Milos, “Loosely Coupled Simulation for Two-Dimensional Ablation and Shape Change,” Journal of Spacecraft and Rockets, Vol. 47, No. 5, 2010, pp. 775-785.

[22]   T. Kanzaka, S. Nozawa, Y. Takahashi, H. Kihara and K. Abe, “Numerical Investigation of Thermal Response of Ablator Exposed to Thermochemical Nonequilibrium Flow,” Proceediongs of the 6th Asian-Pacific Conference on Aerospace Technology and Science, Huangshan, 15-19 November 2009, B2-2.

[23]   S. Gordon and B. J. McBridge, “Computer Program for Calculation of Complex Chemical Equilibrium Computation and Application,” NASA Reference Publication 1311, 1994.

[24]   R. L. Potts, “Application of Integral Methods to Ablation Charring Erosion: A Review,” Journal of Spacecraft and Rockets, Vol. 32, No. 2, 1995, pp. 200-209.

[25]   M. W. Chase Jr., C. A. Davies Jr., J. R. Downey, D. J. Frurip, R. A. McDonald and A. N. Syverud, “JANAF Thermochemical Tables,” Journal of Physical and Chemical Reference Data, Vol. 14, 1985, pp. 535.

[26]   T. Suzuki, K. Fujita, T. Yamada, Y. Inatani and N. Ishii, “Post-Flight TPS Analysis fo Hayabusa Reentry Capsul,” AIAA Paper 2011-3759, 2011.

 
 
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