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固体火箭发动机的点火过程是一个复杂多变的理化过程,具有时间短、升温、升压梯度大等特点。针对固体火箭发动机点火过程中的装药结构完整性问题,文中建立了一套用于分析冲击作用下固体推进剂变形现象的仿真模型。采用RANS和ALE方法,分别对流体域和固体域进行求解,以两场独立交叉耦合迭代的模式实现了仿真过程。以一个推进剂冷流冲击实验作为算例,对仿真模型进行了验证,计算值与测量值间误差不超过10%,仿真模型计算可靠,具有向固体火箭发动机实际点火过程拓展的价值。
Solid rocket engine ignition process is a complex and ever-changing physical and chemical processes, with a short time, heating, step-up gradient and so on. Aimed at the structural integrity of the charge of solid rocket motor during ignition, a set of simulation models for analyzing the deformation of solid propellant under impact were established. The RANS and ALE methods were used to solve the fluid and solid domains, respectively, and the simulation process was implemented in two independent cross-coupled iterative modes. A simulation experiment was carried out by using an experiment on the impact of propellant cold flow as an example. The error between the calculated value and the measured value is less than 10%. The simulation model is reliable and has the value of expanding to the actual ignition process of the solid rocket motor.