| 固体火箭发动机喉径变化辨识 |
| |
| 引用本文： | 方丁酉,张为华.固体火箭发动机喉径变化辨识[J].推进技术,1997,18(2):27-30,49. |
| |
| 作者姓名： | 方丁酉 张为华 |
| |
| 作者单位： | 国防科技大学航天技术系!长沙，410073 |
| |
| 摘 要： | 根据发动机实验得到的燃烧室压强和发动机推力随时间变化数据，考虑了三氧化二铝沉积、消融和喉衬材料烧蚀，建立了喉径变化模型，并用辨识技术得到了喉径变化规律，为发动机性能计算提供了必要的数据，大大提高了性能计算的精度。
|
| 关 键 词： | 固体推进剂火箭发动机 火箭发动机喷管 喉衬 喷管烧蚀计算 |
IDENTIFICATION OF THROAT RADIUS VARIATION FOR SRM |
| |
| Fang Dingyou and Zhang Weihau.IDENTIFICATION OF THROAT RADIUS VARIATION FOR SRM[J].Journal of Propulsion Technology,1997,18(2):27-30,49. |
| |
| Authors: | Fang Dingyou and Zhang Weihau |
| |
| Institution: | Dept. of Aerospace Technology, National Univ. of Defense Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defense Technology, Changsha, 410073 |
| |
| Abstract: | A model of throat radius variation is presented by use of the experimental dataobtained from the SRM test, and the law of throat radius variation is identified by the least squaresmethods. The throat deposition and throat erosion are considered. The identification results are applitedto performance calculations of SRM and the perfermance computational accuracy is greatly improve. |
| |
| Keywords: | Solid propellant rocket engine Rocket engine nozzle Throat insert Nozzle erosion calcuation |
| 本文献已被 CNKI 维普 等数据库收录！ |
| 点击此处可从《推进技术》浏览原始摘要信息 |
| 点击此处可从《推进技术》下载免费的PDF全文 |
