|本期目录/Table of Contents|

[1]柳宁远,崔村燕,辛腾达,等.航天发射场液体推进剂的泄漏扩散模型研究[J].中国安全生产科学技术,2018,14(2):64-69.[doi:10.11731/j.issn.1673-193x.2018.02.010]
　LIU Ningyuan,CUI Cunyan,XIN Tengda,et al.Research on leakage diffusion model of liquid propellant in space launch site[J].JOURNAL OF SAFETY SCIENCE AND TECHNOLOGY,2018,14(2):64-69.[doi:10.11731/j.issn.1673-193x.2018.02.010]
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航天发射场液体推进剂的泄漏扩散模型研究
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《中国安全生产科学技术》[ISSN:1673-193X/CN:11-5335/TB]

卷:
14
期数:
2018年2期
页码:
64-69
栏目:
职业安全卫生管理与技术
出版日期:
2018-02-28

文章信息/Info

Title:
Research on leakage diffusion model of liquid propellant in space launch site
文章编号:
1673-193X(2018)-02-0064-06
作者:
柳宁远1; 崔村燕2; 辛腾达1; 栾骁3
(1. 航天工程大学 研究生管理大队，北京 101416；2. 航天工程大学 航天装备系，北京 101416；3. 中国人民解放军63618部队，新疆 库尔勒 841001 )
Author(s):
LIU Ningyuan1;  CUI Cunyan2;  XIN Tengda1;  LUAN Xiao3
(1. Department of Graduate Management, Aerospace Engineering University, Beijing 101416, China; 2. Department of Space Equipment, Aerospace Engineering University, Beijing 101416, China; 3. 63618 Troops of the People's Liberation Army, Korla Xinjiang 841001, China)
关键词:
扩散模型;  数值模拟;  偏二甲肼;  扩散参数
Keywords:
diffusion model;  numerical simulation;  UDMH;  diffusion parameter
分类号:
X928.7；V511
DOI:
10.11731/j.issn.1673-193x.2018.02.010
文献标志码:
A
摘要:
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。
Abstract:
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.

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备注/Memo

备注/Memo:
原总装备部资助项目（2015SY41A006）
更新日期/Last Update: 2018-03-19