﻿ 固体火箭发动机烤燃数值仿真研究
 舰船科学技术  2021, Vol. 43 Issue (7): 173-177    DOI: 10.3404/j.issn.1672-7649.2021.07.035 PDF

1. 中国船舶重工集团公司第七一三研究所，河南 郑州 450015;
2. 河南省水下智能装备重点实验室，河南 郑州 450015

Research on cook-off numerical simulation of solid rocket motor
WANG Hong-li1,2, YU Wen-hui1,2, LIU Zong-kui1,2, WANG Shi-xin1,2
1. The 713 Research Institute of CSSC, Zhengzhou 450015, China;
2. Henan Key Laboratory of Underwater Intelligence Equipment, Zhengzhou 450015, China
Abstract: In order to reseach the cook-off safety of solid rocket motor (SRM), a cook-off simulation model of SRM was established, and the temperature boundary conditions obtained from the engine shell cook-off test were loaded into the simulation model, and the simulation results of SRM under two kinds of cook-off temperatures were obtained. The simulation results show that the ignition powder of SRM reaches the ignition point first, which is the weak link in the baking safety of SRM.
Key words: solid rocket motor     cook-off     security
0 引　言

1 热分析理论

1.1 热传导

 $q'' = - k\frac{{{\rm{d}}T}}{{{\rm{d}}x}}\text{。}$

1.2 热对流

 $q'' = h({T_S} - {T_B})\text{。}$

1.3 热辐射

 $q = \varepsilon \sigma {A_1}{F_{12}}(T_1^4 - T_2^4)\text{。}$

2 温度载荷试验

 图 1 工况1壳体下表面温度测试曲线 Fig. 1 Test curve of bottom surface of shell temperature under condition 1

 图 2 工况2发动机壳体下表面温度测试曲线 Fig. 2 Test curve of bottom surface of shell temperature under condition 2
3 烤燃仿真模型 3.1 几何模型及网格划分

 图 3 固体火箭发动机有限元模型 Fig. 3 Finite element model of solid rocket motor

3.2 分析设置

1）工况1分析设置

2）工况2分析设置

3.3 载荷施加

 图 4 烤燃模型温度边界条件 Fig. 4 Temperature boundary conditions of cook-off model

 图 5 热辐射边界条件 Fig. 5 Thermal radiation boundary conditions

4 仿真计算结果分析

4.1 工况1结果分析

 图 6 固体火箭发动机不同时刻温度云图（工况1） Fig. 6 Temperature cloud chart of solid rocket engine at different times（condition1）

 图 7 点火药及药柱温度时程曲线（工况1） Fig. 7 Curves of gunpowder temperature and time and grain temperature and time(condition1)

4.2 工况2结果分析

 图 8 固体火箭发动机不同时刻温度云图（工况2） Fig. 8 Temperature cloud chart of solid rocket engine at different times（condition2）

 图 9 点火药及药柱温度时程曲线（工况2） Fig. 9 Curves of gunpowder temperature and time and grain temperature and time(condition2)
5 结　语

 [1] 夏家武, 浦金云, 蔡一轮. 舰艇舱室火灾危险性的评估方法[J]. 海军工程大学学报, 2002, 14(2): 34-38. DOI:10.3969/j.issn.1009-3486.2002.02.009 [2] 原渭兰, 潘浪. 一种舰载导弹固体火箭发动机烤燃过程的数值计算方法[J]. 舰船科学技术, 2009, 31(7): 129-132. YUAN WEI-LAN, PAN LANG. An numerical calculation method on cook-off of solid rocket motor of ship-based missiles[J]. Ship Science and Technology, 2009, 31(7): 129-132. DOI:10.3404/j.issn.1672-7649.2009.07.029 [3] 齐强, 毕世华, 段金锋, 等. 舰载导弹烤燃数值模拟研究[J]. 舰船科学技术, 2006, 28(5): 55-58. OI OIANG, BI SHI-HUA, DUAN JIN-FENG, et al. Cook-off numerical simulation of shipboard missiles[J]. Ship Science and Technology, 2006, 28(5): 55-58. [4] 冯长根, 张蕊, 都振华. 热烤试验研究进展[J]. 科技导报, 2012, 30(33): 68-73. FENG CHANG-GEN, ZHANG RUI, DU ZHEN-HUA. Progress in Cook-off Test[J]. Science and Technology Review, 2012, 30(33): 68-73. DOI:10.3981/j.issn.1000-7857.2012.33.011 [5] 徐松林, 刘文一, 高庆福. 某型高能固体火箭发动机烤燃性能研究[J]. 导弹与航天运载技术, 2017, 2017(6): 24-27. [6] 杨后文, 余永刚, 叶锐. 不同火焰环境下固体火箭发动机烤燃特性数值模拟[J]. 兵工学报, 2015, 36(9): 1640-1646. DOI:10.3969/j.issn.1000-1093.2015.09.006 [7] 吴世永, 王伟力, 苗润, 等. 不同尺寸装药烤燃特性的数值模拟研究[J]. 中国测试, 2016, 42(10): 25-89. DOI:10.11857/j.issn.1674-5124.2016.10.005 [8] 王洪伟, 智小琦, 郝春杰, 等. 升温速率对限定条件下烤燃弹热起爆临界温度的影响[J]. 含能材料, 2016, 24(4): 380-385. DOI:10.11943/j.issn.1006-9941.2016.04.012 [9] 刘文一, 焦冀光. 固体发动机装药热安全性数值分析[J]. 装备环境工程, 2016, 13(2): 129-133. LIU WEN-YI, JIAO JI-GUANG. Numerical Analysis on the Thermal Safety of Solid Rocket Motor Propellant[J]. Equipment Environmental Engineering, 2016, 13(2): 129-133.