摘要
为了优化丁羟(HTPB)推进剂与三元乙丙橡胶(EPDM)绝热层的应用匹配性,采用浸泡实验、接触实验和复合验证等方法,研究了HTPB推进剂中的增塑剂癸二酸二异辛酯(DOS)向EPDM绝热层迁移的特性及其对绝热层性能的影响规律。结果表明:由于极性相近,DOS容易向EPDM绝热层中发生大量迁移,其初期迁移量较显著且饱和迁移量约为52%;EPDM橡胶的结构参数对绝热层硫化胶的耐DOS迁移特性影响不明显;致密的绝热层交联网络有利于减少DOS在其中的迁移量;绝热层厚度增加时,DOS迁移速率变缓,迁入量减小。HTPB推进剂/HTPB衬层/EPDM绝热层粘接体系复合验证结果表明:在推进剂固化过程中DOS已向绝热层发生迁移,导致绝热层的力学性能和烧蚀性能大幅下降;推进剂固化结束后,绝热层的力学性能下降了55%,线烧蚀率增加了20%;70℃贮存30 d时,力学性能下降超60%,线烧蚀率增加了28%;在EPDM绝热层与HTPB衬层之间设置一层环氧基阻迁移层,可以大幅降低推进剂中的增塑剂DOS在绝热层中的迁移量且能够形成良好粘结。
In order to optimize the application matching between HTPB propellant and EPDM insulation,the migration characteristics of plasticizer DOS in HTPB propellant to the EPDM insulation and its effect on the properties of insulation were studied by immersion test,contact test and composite verification.The results show that,due to the similar polarity,a large amount of DOS is easy to migrate to the insulation.The initial migration of DOS is significant and the saturated migration is about 52%.The structural parameters of rubber have no obvious influence on the migration resistance of vulcanized insulation.The dense cross-linked network of insulation can reduce the migration amount of plasticizer DOS in it.When the thickness of insulation increases,the migration rate of DOS slows down and the inflow decreases.HTPB propellant/HTPB liner/EPDM insulation composite verification results show that during the propellant curing process,DOS has migrated to the insulation and cause the mechanical properties and ablative properties of insulation to decrease significantly;After the curing of propellant is finished,the mechanical properties of insulation decrease by 55%and the line ablation rate increase by 20%;When stored at 70℃for 30 days,the mechanical properties decrease by more than 60%and the line ablation rate increase by 28%;An epoxy-based anti-migration layer between the EPDM insulation and the HTPB liner can greatly reduce the migration of plasticizer DOS from propellant to insulation,and form a good bond.
作者
凌玲
周俊
陈雯
隋琦
任雯君
LING Ling;ZHOU Jun;CHEN Wen;SUI Qi;REN Wenjun(Hubei Institute of Aerospace Chemotechnology,Xiangyang 441003,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2024年第1期112-119,共8页
Journal of Solid Rocket Technology
