HTPB复合推进剂燃速对固体火箭发动机内弹道性能影响  

Effects of HTPB Composite Propellant Burning Rate on the Solid Propellant Rocket Motor Internal Ballistic Characteristics

作　　者：徐学文[1] 邓会光[2] 牟俊林[1] 单鑫[1] 

机构地区：[1]海军航空工程学院接改装训练大队,山东烟台264001 [2]海军装备部,北京100841

出　　处：《海军航空工程学院学报》2014年第6期506-510,共5页Journal of Naval Aeronautical and Astronautical University

摘　　要：为准确预测不同贮存期HTPB复合推进剂燃速对固体火箭发动机内弹道性能影响,文章通过燃烧实验测量了贮存2 a、5 a、8 a和10 a发动机推进剂燃速,通过燃烧室-喷管一体化三维流场仿真技术计算了不同贮存期发动机内弹道性能。实验与计算结果表明,贮存时间越长,推进剂燃速越慢,发动机燃烧室内出现压力高峰的时间越滞后,并且压力峰值越下降。In order to accurately predict the effects of HTPB composite propellant burning rate on the internal ballistic char- acteristics with different storing periods of propellant solid rocket motor, the burning rates of propellant stored for two years, five years, eight years and ten years were gained by the burning test, the internal ballistic characteristics of the mo- tor with different storing years being calculated by the integrated 3-D flow field simulation technology of combustion cham- ber and nozzle in the dissertation. As shown in the experiment and calculaiton results, the propellent burning rate became slow, the time appearing pressure wave peak in the combustion chamber being postponed and the peak value becoming small wth the the motor store time increasing.

关 键 词：端羟基聚丁二烯复合推进剂 固体火箭发动机 燃速 内弹道性能 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]