双组元姿控发动机喷管化学反应流场数值模拟  

NUMERICAL SIMULATION ON CHEMICAL REACTING FLOW OF BIPROPELLANT ALTITUDE CONTROLLING THRUSTER NOZZLE

作　　者：蔡国飙[1] 张化照[2] 庄逢甘 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]北京系统工程研究所,北京100076 [3]航天工业总公司科技委,北京100830

出　　处：《宇航学报》2000年第3期6-12,共7页Journal of Astronautics

摘　　要：本文对混合比为 0 9、 1 0、 1 1三种状态下工作的双组元自燃推进剂 (肼 /四氧化二氮 )姿控发动机喷管内化学反应流动进行了数值模拟。数值模拟时采用了弱耦合点隐式方法的数值方法及肼 /四氧化二氮的十二组分、十三个基元反应的有限速率化学反应模型。得到了三种混合比下反应流及混合比为 1 0时冻结流发动机的推力和比推力、喷管中的流动参数及各组分的质量分数。分析表明 ,数值模拟的结果与理论分析一致 ,结果可靠。The chemical reacting flow in the bipropellant altitude controlling thruster nozzle with the mixture ratio of 0 9,1 0 and 1 1 was simulated by using loosely coupled point implicit scheme.In the numerical simulation, the 12 specis,13 step finite rate chemical reaction model of N 2H 4/N 2O 4 was adopted. The thrust and specific impulse of rocket engine and distributions of flow parameters and mass fractions of species were presented. Analysis of the results showed that the numerical simulation results agree well with theory analysis, so it is proved to be reliable. The research provided a theory basis to the altitude controlling thruster nozzle design

关 键 词：双组元推进剂 姿控发动机 化学反应场流场 喷管 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计]