固体火箭发动机C/C喉衬烧蚀率影响参数分析  

Analysis of Influence Parameters on Ablation Rate of Solid Rocket Motor C/C Throat Insert

作　　者：汪太琨 石德磊 鲍福廷[2] WANG Taikun;SHI Delei;BAO Futing(Zhengzhou Mechanical and Electrical Research Institute,CSIC,Zhengzhou 450015,China;National Key Laboratory of Combustion,Flow and Thermo-struicture,Northwesterm Polytechnical University,Xi'an 710072,China)

机构地区：[1]郑州机电工程研究所,郑州450015 [2]西北工业大学固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,西安710072

出　　处：《弹箭与制导学报》2020年第6期125-129,134,共6页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：河北省水下智能装备重点实验室开放基金(D5203190038)资助。

摘　　要：为研究影响喷管喉衬烧蚀的各因素,对固体火箭发动机做出更为精确的性能预示,进行了不同压强和不同推进剂铝含量下的C/C复合材料喉衬烧蚀试验。结果表明,喷管喉衬的烧蚀情况与燃烧室压强正相关,与推进剂中铝含量负相关。前者是由于增大燃烧室压强在提高热流密度的同时又会减弱固相的沉积;后者则是因为氧化铝会在喉衬沉积,进而影响热化学烧蚀情况。In order to study the factors affecting nozzle throat insert ablation and make more accurate performance prediction for solid rocket motor,the throat insert ablation tests of C/C composite materials under different pressure and different propellant aluminum content were carried out.The results show that the ablative condition of nozzle throat insert is positively correlated with combustor pressure and negatively correlated with the aluminum content of propellant.The former is due to the increase of combustor pressure,the increase of heat flux and the decrease of solid deposition.The latter is due to the deposition of alumina in the throat insert,thus affecting the thermochemical ablation.

关 键 词：固体火箭发动机 喉衬 烧蚀 C/C复合材料 含铝推进剂 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]