超期贮存固体火箭发动机使用性能评估

解剖了自然贮存14年的某型发动机,对所得推进剂进行了力学和燃烧性能测试.理论分析中建立了发动机三维内弹道和有限元模型,并根据计算流体动力学(CFD)计算边界网格和有限元模型(FEM)药柱表面网格异构但空间位置一致的特点,开发了发动机内弹道压力转化为药柱有限元载荷的算法,完成了发动机工作过程流场-结构的耦合分析,并对发动机的内弹道和药柱结构完整性进行了评估.试验表明:长期贮存后发动机中端羟基聚丁二烯(HTPB)推进剂力学性能变化体现模量增加和延伸率降低,燃烧性能也有一定变化;计算所得发动机内弹道能完成发射任务,同时发动机药柱的力学性能能保证工作期间的结构完整性,发动机基本满足使用要求. 

Evaluation of performances of an over-storage solid rocket motor

In order to evaluate the performances of an over-storage solid rocket motor(SRM),the solid rocket motor already stored for 14 years was disassembled.The mechanical property and deflagration performances of the solid propellant were measured.The three-dimensional interior ballistic model for igniting process of the SRM was analyzed by numerical simulation.The finite element model(FEM) of the SRM was developed.Based on the grid face of computational fluid dynamics(CFD) mesh and FEM element,the data transfer method from CFD pressure to FEM load was studied.The structural integrity analysis of the SRM was carried out with the fluid-structural coupling technique.It shows that the modulus of the hydroxyl terminated polybutadiene(HTPB) composite propellant after 14 years has been increased,and ε_m decreased.According to the results of interior ballistic simulation and structural integrity analysis,the structural integrity of the grain could be maintained,and the SRM that had been stored for 14 years is applicable for use.