摘要
固体火箭发动机燃烧室内绝热层、人工脱黏层及推进剂药柱,均为高分子材料复合体系。在成型及贮存过程中,湿度是影响丁羟推进剂药柱性能及各界面的联合粘接强度的首要因素。探讨了绝热层、衬层及推进剂药柱在不同环境湿度下的吸湿特性,通过模拟实际生产过程的环境湿度,研究了丁羟推进剂药柱性能及各界面的联合粘接强度变化状况。
The insulation layer, artificial debond layer and propellant grain in solid rocket motor chamber （SRM） are all polymer composite systems. During the molding and storing process, humidity is the foremost factor affecting the characteristics of HTPB propellant grain and adhesion strength between interfaces. The moisture absorption characteristics of insulation layer, liner and propellant grain in different environmental humidities are discussed. The characteristics of HTPB propellant grain and adhesion strength between interfaces were studied by simulating environmental humidity in the practical production process.
出处
《化学推进剂与高分子材料》
CAS
2006年第4期43-45,共3页
Chemical Propellants & Polymeric Materials
关键词
固体火箭发动机
湿度
丁羟推进剂
粘接性能
solid rocket motor
humidity
HTPB propellant
adhesion characteristics
