无喷管助推器喉部侵蚀燃烧规律研究  

Research on throat erosive burning regulations of nozzleless booster

作　　者：陈林泉[1] 毛根旺[1] 霍东兴[1] 何国强[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2009年第2期167-170,共4页Journal of Solid Rocket Technology

基　　金：国防科技重点实验室基金项目(51470010604HT4102)

摘　　要：将X射线高速实时荧屏分析技术用于无喷管助推器的地面试验中,获得了助推器喉部燃面的退移规律,并由此获得了瞬时燃速和侵蚀比。研究表明,无喷管助推器在工作过程中,喉部燃速呈线性下降趋势,侵蚀比约从1.8降低到0.5。对文中研究的推进剂,在1 000 m/s燃气流(喉部)的作用下,当压强大于2.1 MPa时,侵蚀比大于1,并随压强的增大而增加;当压强小于2.1 MPa时,出现负侵蚀现象。文中研究结果为无喷管助推器的性能预示提供了参考。Real-time X-ray radiography technologies were employed in ground test of nozzleless booster. Burning area regrassion rules were obtained through a series of radiographs. And then, burning rate as well as erosion ratio were achieved. The results show that throat burning rate decreases linearly, and the erosive ratio is reduced from 1.8 to 0.5 during nozzleless booster operations. For the mentioned propellant in this paper, erosive ratio is greater than 1.0 and increased with the static pressure when the thorat static pressure is gnrater than 2.1 MPa. However, negative erosion phenomenon can be found when the presure is lower than 2. 1MPa. These results can be used as the references to nozzleless booster performances prediction.

关 键 词：侵蚀燃烧 无喷管助推器 固冲发动机 RTR技术 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]