分析了固液发动机推进剂的燃烧特性和发动机性能特性、与液体和固体火箭发动机的不同，以及研制的技术难度等。
The propellant feature of burning behavior and engine in hybrid engine, the differences to liquid and solid engine and the difficulties of technology in development were analyzed.
为了分析液体推进剂火箭发动机燃烧室中存在的非稳态环境，必须很好地了解稳态状态。
To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood.
针对采用液体推进剂火箭发动机的空间推进系统，推导了系统液路和气路的通用积分形式方程。
The general integral equations are derived for liquid and gas components of space propulsion systems with liquid propellant rocket engine.
应用推荐