摘要
爆炸弹引入扰动是火箭发动机稳定性评定的主要方法,使用计算流体力学方法模拟液氧/甲烷火箭发动机的工作过程,通过添加压力源项与质量源项模拟爆炸弹爆炸过程,得到火箭发动机不稳定性评定试验中,爆炸弹测试火箭发动机时燃烧室的基本流场,指出了结果误差产生的主要原因。结果表明:该方法可以应用在不稳定性评定分析中,有助于减少试验次数。
Explosive bombs is one of the main methods of rocket engine combustion stability rating. The article used Computational Fluid Dynamics (CFD) method to simulate the working process of LOX/methane rocket engine.Bombs exploding process is simulated by adding a pressure source and a energy source into the equation. Results showed the flow fields of LOX/methane rocket engine combustion chamber in the combustion stability rating test. The main reason for the error is pointed out as well.The results showe that the method can be applied in combustion stability rating analysis, which would help to reduce the quantities of tests.
作者
陈峰
丰松江
聂万胜
冯伟
田希晖
Chen Feng;Feng Song-jiang;Nie Wan-sheng;Feng Wei;Tian Xi-hiu(Equipment Academy, Beijing, 101416)
出处
《导弹与航天运载技术》
CSCD
北大核心
2017年第2期40-43,49,共5页
Missiles and Space Vehicles
基金
国家自然科学基金项目(51206185
91441123)
关键词
液氧/甲烷火箭发动机
爆炸弹
数值模拟
稳定性评定
LOX/methane rocket engine
Explosive bombs
Computational fluid dynamics
Combustion stability rating
