Φ200 mm固体火箭发动机复合壳体成型工艺  

Molding Process of Composite Case of Solid Rocket Motor of Φ200 mm

作　　者：王纪霞[1] 马俊[1] 胡大宁 张崇耿[1] 张新航[1] 

机构地区：[1]西安长峰机电研究所,西安710065 [2]陆军驻天水地区军事代表室,天水740000

出　　处：《宇航材料工艺》2012年第6期76-78,共3页Aerospace Materials & Technology

摘　　要：以混合环氧树脂E-51和TDE-85为基体树脂、复合芳香胺为固化剂,采用砂芯模、缠绕等成型工艺,制作的Φ200 mm复合壳体,特性系数PV/W为32.3 km。水压爆破试验结果表明,所设计的碳纤维复合材料发动机壳体满足设计性能指标要求。Composite chamber case of Φ200 mm solid-rocket motor was made by using the two kinds of epoxyresins E-51 and TDE-85, as well as molding process of hermetic and heat-resistance material and molding process offilament winding composites were adopted. The PV / W values of the finished Φ200 mm case are 32. 3 km. The hydrostaticburst test of 36 MPa show that the performances of the filament winding case of solid-rocket motor meet the designrequirements.

关 键 词：复合壳体 基体树脂性能 成型工艺 

分 类 号：TQ327.4[化学工程—合成树脂塑料工业]