| 引用本文: | 谭建国,徐万武,王振国.三组元液体火箭发动机实现单级入轨的优化分析.[J].国防科技大学学报,2003,25(2):9-13.[点击复制] |
| TAN Jianguo,XU Wanwu,WANG Zhenguo.Optimal Analysis of Tripropellant Engine for SSTO[J].Journal of National University of Defense Technology,2003,25(2):9-13[点击复制] |
|
| |
|
|
| 本文已被：浏览 7018次 下载 5890次 |
| 三组元液体火箭发动机实现单级入轨的优化分析 |
| 谭建国, 徐万武, 王振国 |
|
(国防科技大学 航天与材料工程学院，湖南 长沙 410073)
|
| 摘要: |
| 建立了三组元液体火箭发动机性能计算模型、单级入轨可重复使用运载器质量模型和弹道模型，以起飞质量为目标函数，优化得到了实现单级入轨的发动机基本参数。结果显示：三组元发动机性能比氢氧发动机高10%。本研究是三组元发动机系统设计和分析的基础。 |
| 关键词: 单级入轨 三组元液体火箭发动机 优化设计 |
| DOI： |
| 投稿日期：2002-09-05 |
| 基金项目:国家863高技术项目资助 |
|
| Optimal Analysis of Tripropellant Engine for SSTO |
| TAN Jianguo, XU Wanwu, WANG Zhenguo |
|
(College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China)
|
| Abstract: |
| The trajectory model and the mass model of SSTO reusable vehicle and the performance model of tripropellant liquid rocket engine are established. Optimal analysis whose objective is minimizing the vehicle gross mass is performed to attain the engine parameters. Results show that the performance of tripropellant engine is 10% higher than that of LH/LOX engine. This research is the basis of design and analysis of tripropellant propulsion system. |
| Keywords: single stage to orbit tripropellant liquid rocket engine optimal design |
|
|
