Evaluation System for Ablative Material in a High-Temperature Torch

다국어 초록 (Multilingual Abstract)

Ablative thermal protection system (TPS) has been used to protect a vehicle from the heat load experienced during hypersonic or re-entry flights. Typical materials for ablative TPS are carbon–carbon (C/C) composites and carbon–phenolic composites, which have generally been used at working temperatures that are not very high due to surface oxidation. From a material science perspective, modification with ultra-high-temperature ceramic (UHTC) materials or coating with UHTC materials have been undertaken in an attempt to enhance the performance of ablative TPSs for high-temperature applications. As no single facility can reproduce all the aspects of the harsh environments that a vehicle would experience in hypersonic flight, a facility appropriate for the environment of interest is selectively adopted to assess TPS materials. In this study, an evaluation system for ablative material in a high-temperature torch has been developed. As part of the development, cost-effective experiments were conducted using an oxy-kerosene torch. Performance of the C/C test sample was measured, and the flowfield was diagnosed. Numerical simulation of the oxy-kerosene flowfield and the one-dimensional material response have been performed and compared with the test data.

참고문헌 (Reference)

1 "https ://www.nist.gov/"

2 Zhluktov SV, "Viscous shock-layer simulation of airfl ow past ablating blunt body with carbon surface" 13 (13): 50-59, 1999

3 Acurex, "User’s manual, aerotherm chemical equilibrium computer program (ACE 81)" 1981

4 Laub B, "Use of arc-jet facilities in the design and development of thermal protection systems" 2006

5 Milos FS, "Updated ablation and thermal response program for spacecraft heatshield analysis" University of Maryland 2006

6 Corral EL, "Ultra-high-temperature ceramic coatings for oxidation protection of carbon-carbon composites" 91 (91): 1495-1502, 2008

7 Paul A, "UHTC-carbon fibre composites : preparation, oxyacetylene torch testing and characterisation" 33 (33): 423-432, 2013

8 Slavinskaya NA, "Towards kerosene reaction model development: propylcyclohexane, cyC9H18, n-dodecane, C12H26, and Headecane C16H34 combustion" 2010

9 Congon W, "Thermostructural testing of scaled ablativeaeroshell systems using the sandria solar tower facility" 2008

10 Kendall RM, "Thermochemical ablation" AIAA 1965

11 Laud B, "Thermal protection system technology and facility needs for demanding future planetary missions" 239-247, 2004

12 Kratsch KM, "Thermal performance of heat shield composites during planetary entry" 1963

13 Kasen SD, "Thermal management at hypersonic leading edges" University of Virginia 2013

14 Ohlhorst CW, "Thermal conductivity database of various structural carbon-carbon composite materials" NASA 1997

15 Meng S, "The repeated thermal shock behaviors of a ZrB 2 –SiC composite heated by electric resistance method" 29 (29): 44-48, 2011

16 Loehle S, "The plasma wind tunnels at the institute of space systems: current status and challenges" 2016

17 Xian-Hui L, "The infl uence of ablation products on the ablation resistance of C/C-SiC composites and the growth mechanism of SiO2 nanowires" 24 (24): 026103-1-026103-5, 2015

18 Shen X, "The effect of zirconium carbide on ablation of carbon/carbon composites under an oxyacetylene flame" 53 (53): 105-112, 2011

19 Marschall J, "Temperature Jump phenomenon during plasmatron testing of ZrB 2-SiC ultrahigh-temperature ceramics" 26 (26): 559-572, 2012

20 Martin A, "Strongly coupled computation of material response and nonequilibrium flow for hypersonic ablation" 52 (52): 89-104, 2015

21 Upadhyay R, "Steady-State ablation model coupling with hypersonic flow" 2010

22 Park C, "Stagnation-point heat transfer rates for pioneer-venus probes" 13 (13): 33-41, 1999

23 Martin A, "Simulation of pyrolysis gas within a thermal protection system" 2008

24 Fu Q, "Silicon carbide coating to protect carbon/carbon composites against oxidation" 52 (52): 923-927, 2005

25 Walker LS, "Self-Generating high-temperature oxidation-resistant glass-ceramic coatings for C–C composites using UHTCs" 97 (97): 3004-3011, 2014

26 Ahn H, "Response of heatshield material at stagnation point of pioneer-venus probes" 16 (16): 432-439, 2002

27 Moss JN, "Reacting viscous-shock-layer solutions with multicomponent diff usion and mass injection" NASA 1974

28 Karlsdottir SN, "Rapid oxidation characterization of ultra-high temperature ceramics" 90 (90): 3233-3238, 2007

29 Carney C, "Qualitative analysis of hafnium diboride based ultra high temperature ceramics under oxyacetylene torch testing at temperatures above 2100 ℃" 34 (34): 1045-1051, 2014

30 Ahn H, "Preliminary study of the MUSES-C Reentry" 1997

31 Zhang J, "Pre-ablation treatment of carbon/carbon composites to improve the thermal shock resistance for SiC coating under oxyacetylene torch" 355 : 638-643, 2015

32 Smeacetto F, "Oxidation protective multilayer coatings for carbon-carbon composites" 40 : 583-587, 2002

33 Miller-Oana M, "Oxidation behavior of aerospace materials in high enthalpy flows using an oxyacetylene torch facility" 98 (98): 1300-1307, 2015

34 Metzger JW, "Oxidation and sublimation of graphite in simulated re-entry environments" 5 (5): 451-460, 1967

35 Amar AJ, "One-dimensional ablation with pyrolysis gas flow using a full newton’s method and finite control volume procedure" 2007

36 Goulard R, "On catalytic recombination rates in hypersonic stagnation heat transfer" 28 (28): 737-745, 1958

37 Davis RT, "Numerical solution of the hypersonic viscous shock-layer equations" 8 (8): 843-851, 1970

38 Ewing ME, "Numerical modeling of ablation heat transfer" 27 (27): 615-632, 2013

39 Kumar R, "Numerical investigation of gas-surface interactions due to ablation of high-speed vehicles" 53 (53): 538-548, 2016

40 Chen Y, "Navier-stokes solutions with fi nite rate ablation for planetary mission earth reentries" 42 (42): 961-970, 2005

41 Bianchi D, "Modeling of ablation phenomena in space applications" Universita degli Studi di Roma “La Sapienza” 2007

42 Farbar ED, "Modeling ablation of charring heat shield materials for non-continuum hypersonic flow" 2012

43 Jin X, "Microstructure evolution and ablation mechanism of C/C and C/C–SiC composites under a hypersonic flowing propane torch" 19 (19): 1700239-, 2017

44 Yin J, "Microstructure and ablation performances of dual-matrix carbon/carbon composites" 44 (44): 1690-1694, 2006

45 Hill P, "Mechanics and thermodynamics of propulsion" Pearson 1992

46 Cho D, "Manufacturing of needle-punched C/C composite for combustion nozzle" 467-470, 2008

47 Jayaseelan DD, "Laser modified microstructures in ZrB2, ZrB2/SiC and ZrC" 30 (30): 2279-2288, 2010

48 Anderson JD, "Hypersonic and high temperature gas dynamics" AIAA Education Series 2006

49 Mullenix N, "Hypersonic ablation of graphite thermal protection systems with surface defects" 53 (53): 912-929, 2016

50 Miller-Oana M, "High-temperature isothermal oxidation of ultra-high temperature ceramics using thermal gravimetric analysis" 99 (99): 2016-, 2016

51 Wiebenga JE, "High-fidelity material response modeling as part of an aerothermoelastic framework for hypersonic flows" The University of Michigan 2014

52 Larrimbe L, "High heat flux laser testing of HfB 2 cylinders" 100 (100): 293-303, 2016

53 McManus HLN, "High Temperature thermomechanical behavior of carbon-phenolic and carbon-carbon composites, I. Analysis" 26 (26): 206-229, 1992

54 Paul A, "Heat flux mapping of oxyacetylene flames and their use to characterise Cf-HfB 2 composites" 115 (115): 158-165, 2016

55 Suzuki T, "Graphite nitridation in lower surface temperature regime" 2009

56 Bertin JJ, "Fifty years of hypersonics:where we’ve been, where we’re going" 39 (39): 511-536, 2003

57 Funatsu M, "Experimental study of ablation processes of SiC-based materials in air plasma freejets" 8 (8): Pe_41-Pe_46, 2010

58 Leone SA, "Enhancement to integral solutions to ablation and charring" 32 (32): 210-216, 1995

59 Zhang Y, "Effect of preoxidation on the ablation resistance of ZrB 2 –SiC coating for SiC–Coated carbon/carbon composites" 41 (41): 2582-2589, 2015

60 Li H, "Effect of heat flux on ablation behaviour and mechanism of C/C–ZrB 2 –SiC composites under oxyacetylene torch flame" 74 : 265-270, 2013

61 Farhan S, "Effect of density and fibre orientation on the ablation behaviour of carbon-carbon composites" 25 (25): 161-167, 2010

62 Shu-Ping L, "Eff ect of HfC on the ablative and mechanical properties of C/C composites" 517 (517): 61-67, 2009

63 Jayaseelan DD, "Development of multi-layered thermal protection system(TPS)for aerospace applications" 79 : 392-405, 2015

64 Parthasarathy TA, "Development of a test to evaluate aerothermal response of materials to hypersonic flow using a scramjet wind tunnel" 8 (8): 832-847, 2011

65 Pidan S, "Determination of recombination coefficients and spectral emissivity of thermal protection materials" 2004

66 Yang Y, "Deposition and ablation resistance of HfC-based coatings prepared on SiC-coated C/C composites by supersonic atmospheric plasma spraying" 115 (115): 473-482, 2016

67 배진철, "Cyclohexene을 첨가한 PIP 공정 사용 Cf/SiC 복합재의 고밀도화" 한국복합재료학회 26 (26): 322-327, 2013

68 Mills AF, "Convective heat and mass transfer to re-entry vehicles" AFOSR 1978

69 Gordon S, "Computer program for calculation of complex chemical equilibrium compositions and applications" NASA 1994

70 Wiebenga JE, "Computation of multi-dimensional material response coupled to hypersonic flow" 2012

71 Milos FS, "Comprehensive model for multicomponent ablation thermochemistry" 1997

72 McBride BJ, "Coefficients for calculating thermodynamic and transport properties of individual species" NASA 1993

73 Zeng W, "Chemical kinetic simulation of kerosene combustion in an individual flame tube" 5 (5): 357-366, 2014

74 Paglia L, "Carbon-phenolic ablative materials for re-entry space vehicles : plasma wind tunnel test and fi nite element modeling" 90 : 1170-1180, 2016

75 Suzuki T, "Calculation of thermal response of ablator under arcjet flow condition" 21 (21): 257-266, 2007

76 Potts RL, "Application of integral methods to ablation charring erosion, a review" 32 (32): 200-209, 1995

77 Xin Y, "Anti-oxidation behavior of chemical vapor reaction SiC coatings on diff erent carbon materials at high temperatures" 19 (19): 1044-1050, 2009

78 MacLean M, "An equilibrium ablation boundary condition for the data-parallel line-relaxation code" 2013

79 Moyer CB, "Aerotherm equilibrium surface thermochemistry computer program—version 3" Aerotherm 1970

80 McNamara JJ, "Aeroelastic and aerothermoelastic analysis in hypersonic flow : past, present, and future" 49 (49): 1089-1122, 2011

81 Dec JA, "Ablative thermal response analysis using the finite element method" 26 (26): 201-212, 2012

82 Yan M, "Ablative property of C/C–SiC–HfC composites prepared via precursor infi ltration and pyrolysis under 3000 ℃ oxyacetylene torch" 27 (27): 981-987, 2014

83 Yang Y, "Ablation-resistant composite coating of HfC-TaC-SiC for C/C composites deposited by supersonic atmospheric plasma spraying" 7 (7): 379-386, 2016

84 Marguet V, "Ablation-radiation coupling modelling for hayabusa re-entry vehicle" Georgia Tech and Arts et Metiers Paristech 2013

85 Milos FS, "Ablation, thermal response, and chemistry program for analysis of thermal protection systems" 50 (50): 137-149, 2013

86 Yin J, "Ablation properties of C/C–SiC composites tested on an arc heater" 13 (13): 2055-2059, 2011

87 Lundell JH, "Ablation of graphitic materials in the sublimation regime" 13 (13): 1079-1085, 1975

88 Liu L, "Ablation in different heat fluxes of C/C composites modifi ed by ZrB 2 –ZrC and ZrB 2 –ZrC–SiC particles" 74 : 159-167, 2013

89 Zhang X, "Ablation behavior of ZrB 2 -SiC ultra high temperature ceramics under simulated atmospheric re-entry conditions" 68 (68): 1718-1726, 2008

90 Milos FS, "Ablation and thermal response property model validation for phenolic impregnated carbon ablator" 47 (47): 786-805, 2010

91 Chen YK, "Ablation and thermal response program for spacecraft heatshield analysis" 36 (36): 475-483, 1999

92 Li H, "Ablation Resistance of Carbides-Coated C/C Composites" 33 (33): 803-809, 2017

93 Lachaud J, "A short review of ablative-material response models and simulation tools" 2011

94 Reuther J, "A reusable space vehicle design study exploring sharp leading edges" 2001

95 Kendall RM, "A multicomponent boundary layer chemically coupled to an ablating surface" 5 (5): 1063-1071, 1967