HTPB推进剂模压成型工艺探索  

Technology exploration of molding processing for HTPB propellant

作　　者：陈晓明[1] 郑林[1] 赵瑛[1] 

机构地区：[1]西安近代化学研究所,西安710065

出　　处：《固体火箭技术》2013年第6期795-798,共4页Journal of Solid Rocket Technology

摘　　要：对HTPB推进剂进行了模压成型的试验研究。针对不同组分配比的火药,进行了预固化模压成型和无预固化模压成型的试验,探索了工艺参数,对模压样品进行了密度、燃烧性能等测试。结果表明,模压样品密度与浇注样品密度相当,燃烧性能稳定,无预固化模压工艺制备的样品燃速较快。高固体、低稀释剂含量的配方适合于无预固化模压成型工艺,而较低固体含量、较多稀释剂的配方适合于预固化模压成型工艺。HTPB推进剂模压成型,尤其对异型药柱更有独特的优势。The experiment of compression molding conducted on HTPB propellant was studied. Tile experiments with pre-curing molding processing and non-pre-curing molding processing were conducted for different formulas of composite propellant. The tech- nological parameters were explored. The density and combustion performance of samples were tested. The results show that the den- sity of molding samples is the same as casted samples, and its combustion performance is stable. Burning rate of the non-pre-curing is faster than that of the pre-curing samples. High-solid content and low-dilution agent of propellant is suitable for non-pre-curing molding processing. Instead, low-solid content and high-dilution agent of propellant is appropriate for pre-curing molding pl^ocessing. The molding oroeessing technology of HTPB orooellant has unique advantage for propellant with special profile.

关 键 词：HTPB推进剂 模压成型 预固化 复合火药 配方 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]