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摘要: 以流体比容方法和三阶PPM方法为基础，给出了适用于三级气炮超高速发射过程数值模拟的多流计算方法和计算代码MFPPM。利用Sandia实验室一系列的实验装置及其结果对计算代码进行了验证和确认，获得了较好的数值模拟结果（其中最大相对误差为1.07%），同时对冲击波物理与爆轰物理实验室设计的实验装置进行了数值模拟，计算结果与实验结果相差1.04%。为了更好地满足超高压下材料状态方程的测量，提出了一种带汇聚型的改进装置设计，并给出了相应的数值模拟结果。Abstract: A numerical simulation method for calculation of the three-stage light-gas gun impacts on launch flier to hypervelocity is presented. Based on multi-fluid volume of fraction (VOF) and parabolic piecewise method (PPM), a multi-fluid parabolic piecewise method (MFPPM) shock wave physics code is developed to calculate the experimental hypervelocity launchers. To verify and validate our code of MFPPM, some experimental hypervelocity launchers from Sandia National Laboratories are simulated, and the numerical results of flier velocity are excellent in agreement with that experiment (the maximal relative error is 1.07%). Experiment and simulation results of our experiment on the three-stage light-gas gun are given (the maximal relative error is 1.04%). To satisfy well of the high-pressure equation of state (EOS) data measurement, an improved design model from the computation is presented.
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