固体火箭发动机喷管喉衬烧蚀研究进展  

Progress on nozzle throat erosion in solid rocket motor

作　　者：王立武 田维平 郭运强[3] 林志远[1] WANG Liwu;TIAN Weiping;GUO Yunqiang;LIN Zhiyuan(College of Astronautics,Nouthwestern Polytechnical University,Science and Technology on Combustion,Internal Flow and Thermo-Structure Laboratory,Xi'an 710072,China;The Fourth Academy of CASC,Xi’an 710025,China;The 41st Institute of the Fourth Academy of CASC,Xi’an 710025,China)

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072 [2]中国航天科技集团公司四院,西安710025 [3]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2019年第2期135-142,148,共9页Journal of Solid Rocket Technology

摘　　要：在固体火箭发动机工作过程中,由于热化学烧蚀和机械剥蚀的作用,将导致发动机喷管产生烧蚀行为,直接关系到固体火箭发动机的结构可靠性。为了较为深入地了解固体火箭发动机喷管喉衬烧蚀行为及其机理,对国内外固体火箭发动机喷管喉衬烧蚀研究进行了归纳和总结,详细阐明了喉衬烧蚀试验方法、喉衬烧蚀机理及喉衬烧蚀模型;总结了常用的喉衬烧蚀试验方法,并分析了各自优缺点;从热化学烧蚀和机械剥蚀两方面介绍了喉衬烧蚀模型研究进展,分析了目前喉衬烧蚀模型的研究水平。最后,对固体火箭发动机喷管喉衬烧蚀需要开展的工作提出了建议,包括发动机烧蚀率的试验评估方法,喉衬耦合烧蚀计算方法及过载条件对喷管烧蚀的影响规律等,以期为后续研究工作提供一定的借鉴和参考。In the solid rocket motor(SRM)operation process,the nozzle erosion usually occurs because of the chemical and mechanical ablation,which largely determines the reliability of SRM.In order to understand the behavior and mechanism of nozzle throat erosion in SRM,research on nozzle throat erosion in SRM made by scholars have been summarized and analyzed.Experimental methods and research on the mechanism and model of nozzle erosion have been elaborated.Experimental methods of nozzle throat erosion have been summarized,the advantage and disadvantage of each one have been analyzed.The recent progress on the model of nozzle throat erosion has been introduced through chemical and mechanical erosion,and the current level has been analyzed.Finally,some important work regarding nozzle throat erosion in SRM are proposed,including test evaluation method of nozzle ablation,calculation method of nozzle erosion,the influence rule of overload condition to throat ablation,and so on,which may provide a useful reference for the future research work.

关 键 词：固体火箭发动机 喉衬烧蚀 试验方法 烧蚀模型 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]