摘要
为满足瞬间变换内弹道和燃烧产物而能量不变的特殊发动机装药要求，设计了微铝含量复合推进剂配方。探索出小口径薄层药刮涂成型工艺、预固化粘结技术，二次真空加压浇注，实施了大长细比（１２．５／１）发动机薄肉厚内嵌式径向同心双层装药。经地面热试车考核，发动机性能满足设计要求。为今后高装填密度、高质量比的发动机装药开拓出一条新途径。
The composite propellant with mini Al content is studied for the special motor propellant grain, which is required to be constant in energy while the internal ballistic property and combustion products change instantly. The scraping coat technique for the thin layer propellant loading processing in mini inside radius solid rocket motor, precuring bonding technique and secondary vacuum pressure casting are developed and used to load the big slenderness ration (12.5/1) solid rocket motor with thin web, internal insertion radial concentric dual layer propellant. The motor firing test with success met the design requirement for the motor. It is an effective new processing way for loading of the solid rocket motor with high loading density, high propellant mass fraction propellant.
出处
《固体火箭技术》
EI
CAS
CSCD
1999年第2期33-36,共4页
Journal of Solid Rocket Technology
