氢氧火箭发动机动态燃烧稳定性评定技术研究  

Dynamic Combustion Stability Rating of LOX/LH_2 Rocket Engine

作　　者：丁兆波[1] 许晓勇[1] 乔桂玉[1] 陶瑞峰[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《导弹与航天运载技术》2013年第1期38-41,共4页Missiles and Space Vehicles

摘　　要：为了实现氢氧发动机的动态燃烧稳定性试验评定,基于国内外液体火箭发动机动态稳定性评定的相关经验,并结合CPIA655关于稳定性评定的准则,进行了氢氧发动机动态稳定性评定的方案探讨。分析表明,氢氧发动机有必要在全系统热试车状态下进行动态稳定性评定试验。所选定的扰动装置和传感器在喷注器面安装的方案可实现性最好,结构变动最小,可保持试验在原型燃烧室状态下进行,同时扰动效果较好,传感器敏感性较好。In order to carry out dynamic combustion stability rating of a LOX/LH2 rocket engine, the schemes of stability rating for the LOX/LH2 rocket engine are investigated based on the stability rating datum of some rocket engines and the basic criteria of CPIA655, including the evaluation standard, testing method, disturbance method, dynamic pressure testing and structure design. Compared to other schemes, the selected scheme that disturbance device and high frequency pressure sensors install on injector surface has better feasibility and less structural changes, which could ensure the rating test to be carried in a prototype engine, thereby leading to better disturbance efficiency and measure sensitivity.

关 键 词：氢氧发动机 动态稳定性 扰动方法 评定试验 

分 类 号：V434.14[航空宇航科学与技术—航空宇航推进理论与工程]