题目：基于动网格的HMX/GAP/Al固体推进剂的动力学建模与仿真
摘要：本文从诸如燃速，表面温度，气相温度，物质的摩尔分数和比冲等方面研究了不同含量（0-20 wt％）的纳米铝颗粒对HMX/GAP/Al固体推进剂的影响。利用详细动力学机理建立了固相、凝相和气相的数学模型，该模型包括507个气相反应和HMX/GAP/Al燃烧的4个凝相反应（包含气相铝的相变和反应）。基于该模型，利用gPROMS软件包通过动网格方法在不同推进剂成分和工作压力下进行了动态模拟，仿真结果与HMX/Al推进剂燃烧的实验数据非常吻合。之后，本文对HMX/GAP/Al推进剂的燃烧进行了预测，在100atm的工作压力下，20%wt铝含量的推进剂的气相温度为3061K，15%wt含铝量的推进剂比冲为258.53s。此外，结果表明随着压力的增大推进剂的燃速和比冲也增大。根据本文的结果，添加含量范围为15–20 wt％的铝颗粒可显着改善推进剂的燃烧性能。
要点：
1.总结了关于HMX/GAP/Al的反应机理和物性参数
2.气/凝/固相的界面捕捉
Title: Dynamic modeling and simulation of the combustion of aluminized solid propellant with HMX and GAP using moving boundary approach
Abstract: This research describes the influence of nano-sized aluminum with varying contents (0–20 wt%) on the combustion behaviors of HMX/GAP/Al in aspects such as burning rate, surface temperature, gas phase temperature, mole fraction of species, and specific impulse. A rigorous mathematical model is developed for three phases (solid phase, condensed phase, and gas phase) with detailed kinetics. This model consists of 507 gas phase reactions and 4 condensed phase reactions of HMX/GAP/Al combustion. The model also emphasizes the phase transitions and reactions of aluminum in the gas phase. Based on this model, dynamic simulation is carried out at various propellant compositions and operating pressures by means of the moving boundary approach using gPROMS software package. The simulation results are in close agreement with the experimental data at slight marginal errors for HMX/Al combustion, predicting the combustion behaviors for the HMX/GAP/Al system. Accordingly, the model predicts the gas phase temperature of 3061 K for the 20 wt% Al and the specific impulse of 258.53 s for the 15 wt% Al of HMX/GAP/Al propellant under an operating pressure of 100 atm. The increase in burning rate and specific impulse by increasing the pressure is also indicated. According to this study, the addition of aluminum particles with a content range of 15–20 wt% considerably improves combustion behaviors. By dynamic modeling and simulation, a detailed framework for studying the multi-phase combustion of aluminized solid propellant is introduced.
原文链接, CNF, IF 4.12
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