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。
Related to bond polarity, formal charges on atoms, chain reaction theory and the comparison of solid monopropellant combustion and modeling, the "linkage mutualism"mechanism was proposed.
基于凝相机理与热解实验，从分子层面和化学反应的角度，结合价键、形式电荷、链反应等理论和固体单元推进剂的燃烧状况，提出了AP与HMX间的“连锁互动”机制。
Catalyst of the organo-metallic compound (OME) on the combustion and thermal decomposition of HNIW monopropellant was investigated through burning rate measurement, DSC and TG thermal analysis.
通过燃速测定、差示扫描量热技术(dsc)和热失重技术(TG)研究了有机金属化合物催化剂(ome)对六硝基六氮杂异伍兹烷(HNIW)单元推进剂热分解和燃烧性能的影响。
The (investigation) results show that the curves of combustion flame temperature distribution in all combustion course are accurately measured by relative intensity method for monopropellant HNIW.
结果表明，相对强度法能准确地测出单元推进剂HNIW在整个燃烧过程的温度分布曲线，测得的最高燃烧火焰温度低于相应压力下的理论计算温度；
The (investigation) results show that the curves of combustion flame temperature distribution in all combustion course are accurately measured by relative intensity method for monopropellant HNIW.
结果表明，相对强度法能准确地测出单元推进剂HNIW在整个燃烧过程的温度分布曲线，测得的最高燃烧火焰温度低于相应压力下的理论计算温度；
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