一种真空加压绝热工艺方法  

A method of pressurized vacuum insulating process

作　　者：惠亚军[1] 张永侠[1] 贾小峰[1] 

机构地区：[1]中国航天科技集团公司四院七四一六厂,西安710025

出　　处：《固体火箭技术》2013年第4期526-528,共3页Journal of Solid Rocket Technology

摘　　要：提出了一种新的固体发动机内绝热的工艺方法。该方法去掉手工粘贴绝热层,采用固体发动机内绝热层机外预成型,预成型件放置于固体发动机壳体内,采用适当的方法在绝热层预成型件与壳体之间建立真空,并使用气囊给绝热层预成型件加压,在高温条件下固化粘接。此方法对固体火箭发动机壳体一端开口、另一端封闭且机口较小的大长径比固体发动机的绝热尤为适用,解决了手工无法粘贴绝热层的难题。为固体发动机内绝热提供了一种高可靠、高效率、高质量的新方法。A new internal insulating process method of SRM was proposed. Instead of manually paste SRM case, the insulator parts were prefornled outside and then secured onto the internal wall of the case, then bonded to the wall at high temperature with airbag pressurization and vacuumization. This method is especially suitable for tactical motor cases with smaller opening and larger length-to-diameter ratio. This new method can solve the problem when the insulation can not be pasted mannally inside the solid mo- tor, and provide a high-reliable, high-efficiency and high-quality new method for internal insulation of solid rocket motor.

关 键 词：真空 加压 绝热层 预成型 模压成型 绝热工艺 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]