摘要
在文献资料研究的基础上,根据泵压式氢/氧液体火箭发动机的实际特点,考虑发动机性能参数及结构尺寸等影响因素,利用理论推导、统计学及面密度等方法建立发动机质量模型。通过对SSME、RD-0120等8台氢/氧发动机质量的计算,验证了质量模型的合理性。为发动机在系统方案论证时,其质量、性能等参数的估算和优化奠定了基础。
According to the characteristics of the pump-pressurized liquid propellant rocket engine, an engine mass model considering performace parameters and structural size was set up by means of theoretic illation, statistics and surface density. The rationality of the engine mass model was validated by the calculation of SSME, RD-0120 and 6 other different kinds of liquid propellant rocket engines. It established the foundation for optimization of engine mass and performance during the demonstration of an engine system.
出处
《火箭推进》
CAS
2007年第1期1-6,共6页
Journal of Rocket Propulsion
基金
"863基金"
关键词
航空
航天推进系统
氢/氧液体火箭发动机
涡轮泵
质量模型
aerospace propulsion system
hydrogen/oxygen liquid propellant rocket engine
turbopump
mass model
