航天发射场液体推进剂的泄漏扩散模型研究

Research on leakage diffusion model of liquid propellant in space launch site

为了实现对有毒推进剂泄漏扩散浓度的快速估算,对液体推进剂偏二甲肼在发射场泄漏蒸发扩散的实际情况进行理论分析,建立扩散模型,并从泄漏源、沉积效应、地面反射、大气稳定度等方面对扩散模型进行完善;应用数值模拟方法进行仿真,将数值模拟结果与实验数据、理论计算结果进行对比分析。研究结果表明:气体扩散模型与数值模拟及实验结果基本一致,但扩散模型计算结果偏小,这是由于推进剂进行了燃烧和氧化反应,扩散区域温度上升,大气稳定度降低,实际浓度更大。

To realize the rapid estimation on the leakage diffusion concentration of the toxic propellant,the theoretical analysis on the actual situation about the leakage,evaporation and diffusion of the liquid propellant UDMH in the space launch site was carried out.A diffusion model was established and perfected from the aspects of leakage source,deposition effect,ground reflection and atmospheric stability etc.,then the simulation was conducted by using the numerical simulation method,and the results of numerical simulation were compared with the experimental data and the results of theoretical calculation.It showed that the results of gas diffusion model were basically consistent with those of numerical simulation and experiments,but the calculation results of the diffusion model were smaller.The reason was that the combustion and oxidation reaction of the propellant caused the increase of the temperature in the diffusion area,and the atmospheric stability decreased,so the actual concentration was larger.