纤维缠绕复合材料壳体热承载能力分析方法及应用  

Application of thermal load-bearing capacity analysis method for filament wound composite case

作　　者：栗永峰[1] 申志彬[2] 张赋 索晓瑜 于海 

机构地区：[1]中国航天科工集团公司六院,呼和浩特010010 [2]国防科技大学,长沙410073 [3]中国航天科工集团公司六院四十一所,呼和浩特010010

出　　处：《固体火箭技术》2018年第1期89-94,共6页Journal of Solid Rocket Technology

摘　　要：提出了一种固体发动机纤维缠绕复合材料壳体热承载能力分析的工程方法。针对某发动机燃烧室纤维缠绕壳体材料,利用NOL环试样测定了不同温度下的强度保持率,计算了其热承载能力,并结合缩比容器的高温强度试验对其进行了验证,理论分析结果与试验结果误差为7%;最后,利用所提方法预估了某发动机壳体结构的高温承载安全系数,该发动机通过了飞行试验考核,验证了该分析方法的有效性。An engineering method for thermal load-bearing capacity of filament wound composite shell of solid rocket engine is proposed.For the material of filament wound of a certain combustion chamber, the strength retention rate at different temperatures was measured by NOL ring specimens, where the thermal load-bearing capacity was computed. The result was tested by the high temperature strength experimentation of the shrinkage vessel.The error between the theoretical and the experimental results is 7%.Finally, the proposed method is used to predict the high temperature load-bearing safety factor of a certain engine shell structure, and then engine has passed the flight test.h proves that the proposed method is effective.

关 键 词：固体火箭发动机 燃烧室壳体 高温强度 纤维缠绕复合材料 安全系数 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]