Reliability Increase of Base Heating Prediction and Thermal Protection Methodology for Launch Vehicle Upper-Stage

doi:10.23940/IJPE.19.02.P4.387396

Abstract

Abstract:

During spacecraft missionsin some countries all over the world, a number of failures have been observed that were due to the lower reliability of thermal protection of launch vehicles, so the reliability of base heating prediction and thermal protection is very important for successful emissions. The thermal protection of launch vehicles is usually carried out according to the base heating prediction. The base heating environment is a complicated combination of exhaust plume radiation, reversed plume flow convective heating, and engine nozzle radiation. In this paper, the numerical analysis of baseheating is performed to improve the precision of the predictive analysis,and then the flow is modeled using a two-dimensional, Reynolds averaged, and compressible Naive-Stokes equations and DSMC for a chemically frozen mixture gas. After that, the radiation is modeled by using RMC. On the basis of this elaborate base heating prediction, the weaknesses of the thermal protection can be found and the elaborate thermal protection can be realized, so the reliability of base heating prediction and thermal protection methodology can be increased.

Key words: reliability increase, upper-stage, plume heating, predictive analysis, thermal protection

Yiying Bao, Yifu Ding, Pingyang Wang, and Zhenhua Liu. Reliability Increase of Base Heating Prediction and Thermal Protection Methodology for Launch Vehicle Upper-Stage [J]. Int J Performability Eng, 2019, 15(2): 387-396.

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References 19

1	P. Y. Wang, H. F. Lu, H. E. Cheng, “Dsmc Simulation of Plume Backflow from Bipropellant Attitude Control Engine”, Journal of Engineering Thermophysics, Vol. 25, No. 4, pp.640-642, 2004 doi: 10.1023/B:JOGO.0000006653.60256.f6
2	J. Li, L. Yin, L. Yan, “Two-Way Coupled Model for Rarefied Multiphase Flow”, Journal of National University of Defense Technology, Vol. 31, No. 3, pp.6-10, 2009 doi: 10.1007/978-0-387-74660-9_12
3	Z. Y. Tang, B. J. He, G. B. Cai, “Investigation on Boundary Conditions in Decoupled N-S/DSMC Method for Vaccum Plume Simulation of Thrusters”, Journal of Propulsion Technology, Vol. 35, No. 7, pp.897-904, 2014
4	Z. H. Li, H. Z. Zhong, A. P. Peng, J. L. Wu, “A Numerical Method for Simulation Rarefied Two Phase Flow”, Acta Aerodynamica Sinica, Vol. 33, No. 2, pp.266-271, 2015
5	Y. F. Ding, Y. Zhao, P. Y. Wang, “Simulation of High Altitude Solid Rocket Plume based on DSMC Method”, Aerospace Shanghai, Vol. 34, No. 5, pp.110-116, 2017
6	S. K. Dong, Y.Shuai, H. P. Tan, L. H. Liu, “Computation of Radiative Heat Transfer in Participating Media using Backward Monte Carlo Method”, Journal of Harbin Institute of Technology, Vol. 36, No. 12, pp.1602-1604, 2004
7	X. Q. Qi, P. Y. Wang, J. Z. Zhang, Y. Shan, H. E. Cheng, “Reverse Monte Carb Simulation on Infrared of Lobed Nozzle Mixer Plume”, Journal of Shanghai Jiaotong University, Vol. 39, No. 8, pp.1229-1232, 2005
8	F. Yang, P. Y. Wang, Y. Y. Bao, P. Li, “Numerical Simulation on Secondary Launcher Exhaust Plume Base Heating,”Aerospace Shanghai, No. 5, pp.56-51, 2009
9	J. Y. Li, S. K. Dong, H. P. Tan, “Influences of Phase Transition and Carbon Soot Impurity on the Radiative Properties of Alumina Particle Flow”, Journal of Solid Rocket Technology, Vol. 35, No. 4, pp.485-489, 2012
10	P. J. Sun, D. B. Wang, F. Yang, Y. R. Zhou, Y. Y. Bao, W. D. Zhang, et al., “Numerical Simulation and Flight Test Validation of a Launch Vehicle Altitude Engine Exhaust Plume Base Heating”, Aerospace Shanghai, Vol. 33, No. S1, pp.23-28, 2016
11	I. D. Boyd, P. F. Penko, D. L.Meissner, “Numerical and Experimental Investigations of Rarefied Nozzle and Plume Flows of Nitrogen,”in Proceedings of the 26 ^th Thermophysics Conference, pp.91-1363, 1991 doi: 10.2514/6.1991-1363
12	I. D. Boyd, P. F. Penko, D. L. Meissner, K. J. DeWitt,“Experimental and Numerical Investigations of Low-Density Nozzle and Plume Flows of Nitrogen,” AIAA Journal, Vol. 30, No. 10, pp.2453-2460, 1992 doi: 10.2514/3.11247
13	O. Kramer, “Evaluation of Thermal Radiation from the TITAN III Solid Rocket Motor Exhaust Plumes,”in Proceedings of the 5th Thermophysics Conference,Los Angeles,California, pp.1-9, 1970 doi: 10.2514/6.1970-842
14	J. D. George and I. D. Boyd,“Simulation of Nozzle Plume Flows using a Combined CFD-DSMC Approach,” AIAA, pp.99-3454, 1999 doi: 10.2514/6.1999-3454
15	G. A. Bird, “Molecular Gas Dynamics and the Direct Simulation of Gas flows, ”Clarendon Press, 2003
16	O. Kramer, “TITAN III Convective Base Heating from Solid Rocket Motor Exhaust Plumes, ” inProceedings of AIAA/SAE 8th Joint Propulsion Specialist Conference, New Orleans,Louisiana,AIAA, pp.1-7, 1972 doi: 10.2514/6.1972-1169
17	T. F. Greenwood, “Development of Space Shuttle BaseHeating Methodology and Comparison with Flight Data,” in Proceedings of the JANNAF 13th Plume Technology Meeting,Chemical Propulsion Information Agency, CPIA-357, Vol.1, pp.67-82, Houston, Texas, April 1982
18	T. F. Greenwood, Y. C. Lee, R. L. Bender, R. E Carter, “Space Shuttle Base Heating”, Journal of Apacecraft and Rockets, Vol. 21, No. 4, pp.339-345, 1984
19	T. F. Greenwood, D. C. Seymour, R. L. Bender, “BaseHeating Prediction Methodology used for the Space shuttle,” in Proceedings of the JANNAF 10th Plume Technology Meeting,Chemical Propulsion Information Agency, CPIA-291, Vol.2, pp.253-312, SanDiego, California, December 1977

Serial number of the typical position	Heat flux（kW/m²）
Serial number of the typical position	Radiative heat flux of the nozzle	Radiative heat flux of the plume	convective heat flux of the plume	Total heat flux
1	10.9	0.224	0.01	11.13
2	15.6	0.162	0.21	15.97
3	17.7	0.155	0.39	18.25
4	9.8	0.172	0.50	10.47
5	12.96	0.182	1.14	14.28
6	12.87	0.157	1.38	14.40
7	8.7	0.193	0.47	9.36
8	12.04	0.144	0.24	12.42
9	5.76	0.312	0.95	7.02
10	4.82	0.232	1.09	6.14

Serial number of the heat flux sensor	the computed total heat flux (kW/m²)	the measured total heat flux (kW/m²)	Percentage error
1	11.6	5.6~10.1	14.9%
2	22.6	16.7~22.3	1.3%