固体火箭冲压发动机燃气流量调节特性  

Regulating property of the flow in a solid ducted rocket

作　　者：鲍文[1] 牛文玉[1] 陈林泉[2] 于达仁[1] 孙有田 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001 [2]中国航天科技集团公司四院,陕西西安710025 [3]海军驻航天三院军代表室,北京100074

出　　处：《推进技术》2007年第4期433-436,共4页Journal of Propulsion Technology

摘　　要：为了研究固体火箭冲压发动机燃气流量调节特性,对固体火箭冲压发动机燃气流量控制阀的5种不同开度下的二维流场进行了数值模拟,分析得出了补燃室压力、阀门开度对流量控制阀流场分布、阀头轴向受力和通过控制阀的燃气质量流量的影响,基于模拟得到的数据,分析得到了固体火箭冲压发动机燃气流量调节特性的参数表达式,该表达式可以用来作为固体火箭冲压发动机燃气流量调节的参考。In order to study the regulating property of the flow in a solid ducted rocket, the 2-D internal flow-field of five different openings for flow control valve of solid ducted rocket was simulated. The effects of pressure in secondary combustor and openings on flow field on flow control valve, axial force of valve head and flowrate through the flow control valve were analyzed. Based on the data from simulation, the regulating property parametric expression of flow control valve in solid ducted rocket is obtained. This parametric expression can be the reference of flow regulating for solid ducted rocket.

关 键 词：固体燃料冲压发动机 流量控制阀 数值仿真 调节特性^+ 

分 类 号：V235.2[航空宇航科学与技术—航空宇航推进理论与工程]