飞行加速度对固体火箭发动机前封头绝热层烧蚀特性影响研究

EFFECTS OF FLIGHT ACCELERATION ON EROSION CHARACTERISTICS OF FORWARD DOME INSULATION OF SOLID ROCKET MOTORS

对固体火箭发动机前封头绝热层在加速度环境中的炭化烧蚀特性进行了实验研究，研制了烧蚀试验发动机及相应的离心试验台，用ＮＢＲ，ＥＰＤＭ绝热层模拟实际烧蚀环境进行了不同轴向加速度条件下的烧蚀试验，得到了飞行加速度对绝热层炭化烧蚀率影响规律和经验关系式。

The charring ablation characteristics of solid rocket motors forward dome insulation in the acceleration environment were investigated by experiments.The ablation test motor and corresponding centrifugal ignition test device were researched and developed.By simulating actual ablation environment,the ablation tests of NBR and EPDM insulation were performed in different axial acceleration conditions.The influential regularities and empirical formulas were obtained