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。
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.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2003年第2期9-13,共5页
Journal of National University of Defense Technology
基金
国家863高技术项目资助
关键词
单级入轨
三组元液体火箭发动机
优化设计
single stage to orbit
tripropellant liquid rocket engine
optimal design
