摘要
对航天用XM-23密封剂进行了仔细研究。重点考虑了其作为阻尼剂在航天光学遥感器反射镜组件中的应用情况,分析了其各组分构成及功能,合理选择了各组分质量配比,优化了和胶过程中各组分的添加顺序,形成了常温常压初固化、常温常压基本固化、真空高温后固化的固化工艺。最终得出了一种比较理想的可用于空间反射镜组件结构微应力密封的使用工艺路线。试验数据表明,该使用工艺路线时间短,内应力小,各组分配比合理,达到了空间项目中对密封剂微应力的使用要求,因而可以广泛应用于空间结构。
The XM-23 sealant for space application was studied carefully.The application of it in the mirror subassembly of a space optical remote sensor as a damping agent was mainly considered.Its composition and function were analyzed.The mass ratio of each component was selected reasonably and the adding sequence of each composition in the sealant mixing process was optimized.Finally,an ideal curing process route for sealing the mirror subassembly of a space optical remote sensor in micro-stress was obtained.The testing result showed that the process route had the features of less time,less internal stress and reasonable composition ratio.It met the micro-stress requirements of the sealant used for space application.Therefore,it could be widely used in the structures for space application.
出处
《红外》
CAS
2012年第7期11-15,共5页
Infrared
基金
中国科学院三期创新工程资助项目(07423JN70)
