双脉冲固体发动机喷管传热烧蚀特性

张晓光; 刘宇; 王长辉

双脉冲固体发动机喷管传热烧蚀特性

北京航空航天大学宇航学院,北京 100191

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出版历程
- 收稿日期: 2011-07-04
- 刊出日期: 2012-06-28

Characterization of nozzle thermal and ablation response in dual-pulse solid rocket motors

School of Astronautics, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 为了研究双脉冲固体发动机喷管的传热烧蚀特性,由燃烧室压强及发动机推力试验曲线得到了喷管喉径的瞬变值,由FLUENT流体计算软件进行流固耦合传热烧蚀计算,得到了喷管瞬态温度分布、绝热材料热解炭化情况及碳/碳(C/C)喉衬瞬态烧蚀率,分析了脉冲工作过程及脉冲间隔时间对喷管传热烧蚀的影响.计算结果表明,脉冲工作过程中,绝热材料热解线、炭化线向材料内部扩展,喉衬烧蚀率不断增大;脉冲间隔时间内,喷管材料内部的导热使各处温差减小,温度趋于一致;第一脉冲的传热烧蚀与脉冲间隔的材料导热使第二脉冲工作时喉衬整体热沉小、内壁初始温度高、表面粗糙度大,从而导致较高烧蚀率.
- 双脉冲固体发动机 /
- 喷管 /
- 传热 /
- 烧蚀 /
- 流固耦合
Abstract: In order to investigate the nozzle thermal and ablation characteristics in dual-pulse solid rocket motors,the transient value of the throat diameter was obtained from the pressure and thrust measurements.Furthermore,the in-depth thermal response,pyrolysis/char profiles and surface recession of the nozzle assembly were predicted through fully coupled fluid-solid analysis using the commercial code FLUENT.Results show that during pulse operation,the insulation material pyrolysis/char profiles expand and the nozzle insert erosion rate increases.During pulse separation,heat conduction in the material leads to the decrease in the material temperature difference.The heat transfer and ablation processes of pulse 1 and pulse separation make the nozzle insert exhibit small heat sink,high surface temperature and large surface roughness,which would result in higher throat erosion rate when pulse 2 operates.
- dual-pulse solid rocket motor /
- nozzle /
- heat transfer /
- erosion /
- fluid-solid coupling

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参考文献(12)

[1]	闵斌.防空导弹固体火箭发动机设计[M].北京:宇航出版社,1993.
[2]	Myers J,Jordan F.Characterizing nozzle behavior as a function of materials and configuration .AIAA 84-1310,1984.
[3]	李宜敏,张中钦,张远君.固体火箭发动机原理[M].北京:北京航空航天大学出版社,1991.
[4]	余贞勇.固体火箭发动机喷管喉径瞬变值的计算和预示[J].固体火箭技术,1993(4):27-33. YU Zhenyong.The calculation and prediction of transient value of nozzle throat radius[J].Journal of Solid Rocket Technology,1993(4):27-33.(in Chinese)
[5]	陶文铨.数值传热学[M].西安:西安交通大学出版社,2001.
[6]	蔡体敏,王思民.高硅氧增强塑料烧蚀模型中热解层厚度的探讨[J].推进技术,1989,2(1):10-13. CAI Timin,WANG Simin.A discussion on the thickness of pyrolysis layer in the ablation model for silica-phenolics composite material[J].Journal of Propulsion Technology,1989,2(1):10-13.(in Chinese)
[7]	蔡体敏.固体火箭发动机工作过程的数值分析[M].西安:西北工业大学出版社,1991.
[8]	Thakre P,Yang V.Chemical erosion of carbon-carbon/graphite nozzles in solid-propellant rocket motors[J].Journal of Propulsion and Power,2008,24(4):822-833.
[9]	Back L H,Massier P F,Gier H L.Convective heat transfer in a convergent-divergent nozzle[J].International Journal of Heat and Mass Transfer,1964,7(5):549-568.
[10]	Keizers H L J,Veraar R G.Analysis of heat transfer in nozzles .AIAA 96-3290,1996.
[11]	Acharya R,Kuo K K.Numerical simulation of graphite nozzle erosion with parametric analysis .AIAA 2010-6846,2010.
[12]	Thakre P,Yang V.Effect of surface roughness and radiation on graphite nozzle erosion in solid rocket motors .AIAA 2009-5275,2009.