喷管热环境对碳基材料喉衬烧蚀率的影响
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摘要
采用装有羟基聚丁二烯(HTPB)与高能推进剂的多种规格固体火箭发动机,对工程应用的5种炭/炭(C/C)复合材料和2种石墨喉衬进行地面点火试验。揭示碳基材料喉衬烧蚀率与喷管热环境的燃气特性、燃烧室压强,以及材料本体特性等三要素的关联度,并与其他国家同类型材料进行了对比。结果表明,喷管热环境的燃气氧化性组分浓度和燃烧室压强对碳基材料喉衬烧蚀率有较大影响。压强是影响烧蚀率的第一要素,压强增加1倍,烧蚀率增大1. 8～2. 6倍;燃气氧化性组分浓度是影响烧蚀率的第二要素,HTPB H_2O的摩尔浓度比高能推进剂高1. 26倍,因而烧蚀率增大51. 6%～65. 1%。在碳基材料喉衬中烧蚀率最低的是热解石墨;其次是整体毡C/C、针刺炭纤维C/C、轴编4D C/C、绕纱(穿刺) 3D C/C及T705石墨等处于同一水平;而径编4D C/C喉衬烧蚀率偏高。整体而言,中国碳基喉衬材料与其他国家同类材料相比,其烧蚀率基本相当或略优。
Solid rocket motors using five different C/C composites( radially woven 4 D C/C,axially woven 4 D C/C,integral felt C/C,needle felt C/C and punctured 3 D C/C) and two kinds of graphite( T705 graphite and an anisotropic pyrolytic graphite with a density of 2. 18 g/cm~3,a porosity of 1% and graphene layers perpendicular to throat surface) as the throat inserts were propelled by hydroxyl terminated polybutadiene or a high energy fuel to test the ablation rates of the throat inserts. The effect of nozzle thermal environment( propellant type and combustion chamber pressure) on the ablation rates of the throat insert materials was investigated under identical conditions. Results show that the ablation rates of the carbon materials are closely related to the concentration of the oxidative gases( H_2 O and CO_2) and the chamber pressure. The chamber pressure is of primary importance,and doubling it leads to an increase of ablation rates by 1. 8-2. 6 times. The ablation rates using the hydroxyl terminated polybutadiene propellant are 51. 6%-65. 1% higher than those using the high energy propellant because the concentration of oxidizing H_2 O in the former is 1. 26 times higher than that in the latter. The pyrolytic graphite has the lowest ablation rate followed by the integral felt C/C,needle felt C/C and axially woven 4 D C/C. The radially woven 4 D C/C has the highest rate,and the punctured 3 D C/C and T705 graphite have similar ablation rates. The ablation rates of the five composites and two graphites made in China are similar or superior to the C/C composites and Graphnol graphite made in other countries.
Solid rocket motors using five different C/C composites( radially woven 4 D C/C,axially woven 4 D C/C,integral felt C/C,needle felt C/C and punctured 3 D C/C) and two kinds of graphite( T705 graphite and an anisotropic pyrolytic graphite with a density of 2. 18 g/cm~3,a porosity of 1% and graphene layers perpendicular to throat surface) as the throat inserts were propelled by hydroxyl terminated polybutadiene or a high energy fuel to test the ablation rates of the throat inserts. The effect of nozzle thermal environment( propellant type and combustion chamber pressure) on the ablation rates of the throat insert materials was investigated under identical conditions. Results show that the ablation rates of the carbon materials are closely related to the concentration of the oxidative gases( H_2 O and CO_2) and the chamber pressure. The chamber pressure is of primary importance,and doubling it leads to an increase of ablation rates by 1. 8-2. 6 times. The ablation rates using the hydroxyl terminated polybutadiene propellant are 51. 6%-65. 1% higher than those using the high energy propellant because the concentration of oxidizing H_2 O in the former is 1. 26 times higher than that in the latter. The pyrolytic graphite has the lowest ablation rate followed by the integral felt C/C,needle felt C/C and axially woven 4 D C/C. The radially woven 4 D C/C has the highest rate,and the punctured 3 D C/C and T705 graphite have similar ablation rates. The ablation rates of the five composites and two graphites made in China are similar or superior to the C/C composites and Graphnol graphite made in other countries.
引文
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[2]D.L.Schmidt,K.E.Davidson,L S Theibet.Unique application of carbon-carbon composite material[J].SAM PE,1999,35(4):51-62.
[3]苏君明.C/C复合材料喉衬的研究与发展[J].炭素科技,2001,11(1):6-11.(SU Jun-ming.Research and development of C/C throat insert material[J].Carbon Science and technology,2001,11(1):6-11.)
[4]苏君明.高效高冲质比C/C喷管的应用与进展[J].新型炭材料,1996,11(3):18-23.(SU Jun-ming.Application and development of C/C nozzle with high specific thrust rate[J].New Carbon M aterials,1996,11(3):18-23.)
[5]刘建军,苏君明,陈长乐.炭/炭复合材料烧蚀性能影响因素分析[J].炭素,2003,(2):15-19.(LIU Jian-jun,SU Jun-ming,CHEN Chang-le.Study on factors affecting ablative performance of C/C composites[J].Carbon(Chinese),2003,(2):15-19.)
[6]黄海明,杜善义,吴林志,等.C/C复合材料烧蚀性能分析[J].复合材料学报,2001,18(3):76-80.(HUANG Hai-ming,DU Shan-yi,WU Lin-zhi,et al.Analysis of the Ablation of C/C Composites[J].Acta M aterial Composite Sinica,2001,18(3):76-80.)
[7]HOU Xiao,CHENG Wen,Chen Ni.Preparation of a high performance carbon/carbon composite throat insert w oven with axial carbon rods[J].New Carbon M aterials,2013,28(5):355-362.
[8]王书贤,陈林泉,刘勇琼.C/C喉衬材料烧蚀试验方法研究[J].固体火箭技术,2007,30(2):170-172.(WANG Shu-xian,CHEN Lin-quan,LIU Yong-qiong.Investigation on ablative property test methods for C/C throat insert material[J].Journal of Solid Rocket Technology,2007,30(2):170-172.)
[9]苏君明,周绍建,李瑞珍,等.工程应用C/C复合材料的性能分析与展望[J].新型炭材料,2015,30(2):106-114.(SU Jun-ming,ZHOU Shao-jian,LI Rui-zhen,et al.A review of carbon-carbon composites for engineering applications[J].New Carbon M aterials,2015,30(2):106-114.)
[10]苏君明,谢乔,冯婧,等.喉衬用石墨材料的性能和功能评价[J].固体火箭技术,2015,38(4):554-561.(SU Jun-ming,XIE Qiao,FENG Jing,et al.The evaluation of performance and function of graphite material for throat insert[J].Journal of Solid Rocket Technology,2015,38(4):554-561.)
[11]张名大.热解石墨栅极[J].炭素,1980(1):1-8.(ZHANG Ming-da.Grid of pyrolytic graphite[J].Carbon(Chinese)1980(1):1-8.)
[12]Borie V.An aerotheramal chemical analysis of carbon-carbon nozzle regression in solid-propellant rocket motor[R].AIAA-88-3346.
[13]Thakre P,Yang V.A comprehensive model to predict and mitigate the erosion of carbon-carbon/graphite rocket nozzles[R].AIAA 2007-5777.
[14]Daniele Bianchi,Francesco Nasuti,Emanuele Martelli.Coupled analysis of flowand surface ablation in carbon-carbon rocket nozzles[R].AIAA 2008-3912.
[15]D.E.Whitney,K.P.Hennessey.Development of an alternate nozzle for the M K 111 tomahaw k booster rocket motor[R].AIAA 92-3555.
[16]G C Lamere.MX first stage nozzle development[C].AO/A103844.
[17]M.Bussiere.M.Prel.Ariane V solid rocket booster nozzle development status[R].AIAA-94-3063.
[18]刘建军,李铁虎,郝志彪.喉衬热环境与碳/碳复合材料的烧蚀[J].宇航材料工艺,2005(1):42-48.(LIU Jian-jun,LI Tie-hu,HAO Zhi-biao.Throat thermal ambient and ablation of C/C composites[J].Aerospace M aterial Process,2005(1):42-48.)
[19]冉红星,崔红,郝志彪,等.碳基体结构状态对C/C复合材料抗烧蚀性能的影响[J].炭素,2002(4):20-25.(RAN Hong-xing,CUI Hong,HAO Zhi-biao,et al.Influence of carbon matrix structure on antiablative performances of C/Ccomposites[J].Carbon(Chinese)2002(4):20-25.)
[20]苏君明,邵海成,肖志超,等.低烧蚀率针刺炭纤维炭/炭复合材料喉衬的制备与性能研究[J].炭素技术,2013,32(6):A1-A5.(SU Jun-ming,SHAO Hai-cheng,XIAO Zhi-chao,et al.Preparation and properties of needling carbon/carbon composites throat with lowablation rate[J].Carbon Techniques,2013,32(6):A1-A5.)
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