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N a solid or liquid rocket propellant containing both the fuel and the oxidizer 单元推进剂
Thermal control of monopropellant catalytic decomposition hydrazine engines in important portion of space propulsive system.
单组元肼分解发动机的热控制与热分析是空间推进系统重要组成部分。
The research emphasis is restartable nitrous oxide monopropellant thruster suitable for keeping the position and phase of small satellite.
研究重点是可多次启动的一氧化二氮单元推进剂推力室，适用于小卫星的位置保持和相位保持。
Based on a thermal model of monopropellant thrust chamber system including its components such as adiabatic frame, catalyst bed, nozzle etc.
建立了单组元发动机推力室系统（包括结构部件如隔热框、催化床、喷管等）的传热模型。
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