| 引用本文: | 雷建南,谭松林.液体火箭发动机烧蚀冷却推力室室壁温度响应的计算.[J].国防科技大学学报,1988,10(2):1-13.[点击复制] |
| Lei Jiannan,Tan Songlin.Wall Temperature Response Calculation of Ablative Cooling Chamber of LRE[J].Journal of National University of Defense Technology,1988,10(2):1-13[点击复制] |
|
| |
|
|
| 本文已被：浏览 5328次 下载 5697次 |
| 液体火箭发动机烧蚀冷却推力室室壁温度响应的计算 |
| 雷建南, 谭松林 |
|
(航天技术系)
|
| 摘要: |
| 本文对液体火箭发动机烧蚀冷却推力室的冷却机理进行了分析，较为全面地考虑了影响温度场的主要因素，利用六点中心差分建立了离散数学模型，并对室壁温度响应进行了计算，得到了烧蚀速率和侵蚀速率等。所得结果可供设计推力室时参考。 |
| 关键词: 液体火箭发动机，烧蚀冷却，温度响应计算 |
| DOI： |
| 投稿日期：1987-08-01 |
| 基金项目: |
|
| Wall Temperature Response Calculation of Ablative Cooling Chamber of LRE |
| Lei Jiannan, Tan Songlin |
|
(Department of Aerospace Technology)
|
| Abstract: |
| In this paper, the cooling mechanism of the ablative cooling chamber of LRE is analyzed, and the main factors of its response to the temperature field are considered in full. The dispersed mathematical model is founded by using the central difference of six points. The wall temperature response is calculated and the ablative and erosive rate is obtained. The obtained result is for a reference in designing the thrust chamber. |
| Keywords: Liquid Propellant Rockek Engines,Ablative cooling,Temperature response calculation |
|
|
|
|
|
