固体火箭发动机C/C复合材料烧蚀试验技术研究  

Research on Ablation Test Technology of C/C Composites in Solid Rocket Motor

作　　者：高勇[1,2] 查柏林 王金金 嵇阿琳 王玲玲[1] 廉云清[1] 肖春[1] GAO Yong;ZHA Bailin;WANG Jinjin;JI ALing;WANG Lingling;LIAN Yunqing;XIAO Chun(Xi’an Aerospace Composites Research Institute,Xi’an 710025,Shaanxi,China;Rocket Force University of Engineering,Xi’an 710025,Shaanxi,China)

机构地区：[1]西安航天复合材料研究所,西安710025 [2]火箭军工程大学,西安710025

出　　处：《高科技纤维与应用》2020年第4期1-7,共7页Hi-Tech Fiber and Application

摘　　要：碳/碳(C/C)复合材料是一种特别具有性能可设计性和抗热震性的先进复合材料,它以优异的超高温力学性能、耐烧蚀性能及抗热冲击性能,成为固体火箭发动机喷管喉衬的首选材料。为了深入了解固体火箭发动机喉衬材料的烧蚀行为与烧蚀机理,本文对现阶段应用较广泛、较成熟的几种C/C复合材料耐烧蚀性能的测试表征技术进行了归纳与总结,概述这几种测试表征方法在固体火箭发动机喉衬材料耐烧蚀性能表征应用方面存在的优缺点,比对分析了其烧蚀测试水平同原型发动机烧蚀实测值的差距,并对未来固体火箭发动机喉衬C/C复合材料烧蚀试验表征技术的发展方向提供一定的借鉴和参考。Carbon/carbon(C/C)composite is a kind of advanced material with good designable characteristic and thermal shock resistance.As its superior characteristics of excellent ultra-high mechanical property,ablation property,good thermal shock resistance and so on,the C/C composites make them the preferred materials for throat in solid rocket motor.In order to understand the ablation behavior and mechanism of nozzle throat erosion in solid rocket motor,several widely used ablation experimental techniques of its ablation performances have been summarized and analyzed,and the advantage and disadvantage as well as the current level of each one have been analyzed,which may provide a useful reference for the future development direction of ablation experimental technique for C/C composites in solid rocket motor.

关 键 词：固体火箭发动机 C/C复合材料 喉衬烧蚀 烧蚀试验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]