中心进气式固体火箭冲压发动机试验研究  

Experimental study on solid rocket ramjet with central air-inlet mode

作　　者：郑凯斌[1] 陈林泉[1] 张胜勇[1] 

机构地区：[1]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2007年第2期124-127,共4页Journal of Solid Rocket Technology

摘　　要：设计了采用中心进气式固冲试验发动机,通过直连式试验考核了其点火和燃烧性能,对其反应流场进行了数值模拟,并与试验结果进行了对比。研究结果表明,这种新型结构的冲压发动机可行;碳氢贫氧推进剂燃烧效率高于含硼贫氧推进剂,而能量相对较低;采用的数值计算模型和方法适用于分析中心进气式固冲发动机反应流场。A test solid rocket ramjet with central air-inlet mode was designed, and its ignition and combustion performances were examined in the direct-connected test. The reacting flow field of the motor was numerically simulated, and the results were compared with test data. The analysis shows that the new motor structure is practicable. Compared with the low-oxygen boron propellant, the hydrocarbon low-oxygen propellant possesses higher combustion efficiency, but lower power. Numerical calculation model and method are applicable to analyzing reacting flow field of the solid rocket ramjet with central air-inlet mode.

关 键 词：固体火箭冲压发动机 中心进气式 燃烧效率 数值模拟 

分 类 号：V435.1[航空宇航科学与技术—航空宇航推进理论与工程]