| 深空探测发动机热环境研究 |
| |
| 引用本文： | 魏超,张忠利.深空探测发动机热环境研究[J].航空动力学报,2010,25(5):1139-1144. |
| |
| 作者姓名： | 魏超 张忠利 |
| |
| 作者单位： | 1. 西北工业大学,航天学院,西安,710072
2. 航天推进技术研究院,西安航天动力研究所,西安710100 |
| |
| 摘 要： | 对深空探测发动机热环境进行了分析,发现深空探测发动机喷管将给探测器辐射较高热量;为了尽可能阻止热量散发至探测器,拟采用热阻材料;采用热阻材料后,喷管壁温较没有热阻材料时高,但还在使用范围之内.热防护分析方法经过了地面试车验证,计算结果与试车测量值符合较好.
|
| 关 键 词： | 液体火箭发动机 深空探测 热防护 数值仿真 |
| 收稿时间： | 1/8/2010 12:00:00 AM |
| 修稿时间： | 3/5/2010 12:00:00 AM |
Investigation on thermal environment for deep-space-exploration liquid rocket engine |
| |
| WEI Chao and ZHANG Zhong-li.Investigation on thermal environment for deep-space-exploration liquid rocket engine[J].Journal of Aerospace Power,2010,25(5):1139-1144. |
| |
| Authors: | WEI Chao and ZHANG Zhong-li |
| |
| Institution: | School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;Xi'an Aerospace Propulsion Institute, Academy of Aerspace Propulsion Technology, Xi'an 710100, China |
| |
| Abstract: | The thermal environment for deep-space-exploration liquid rocket engine (LRE) was analyzed. It was found that high heat flux could be eradiated to the explorer from the nozzle of LRE. The thermal resistance material was used to prevent heat radiation onto the explorer. When the engine was coated with thermal resistance material,the nozzle wall temperature could be higher than wall temperatures without coating. The current analysis showed that,the increased nozzle wall temperature was still in the allowable range for engine thermal protection. The computational methods of current paper were validated by hot-fire testing. The results were in good agreement with hot-fire measurements. |
| |
| Keywords: | liquid rocket engine(LRE) deep-space-exploration thermal protection ntLlmer cal simillation |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
