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。
The research emphasis is restartable nitrous oxide monopropellant thruster suitable for keeping the position and phase of small satellite.
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.
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（OM E）对二硝酰胺铵（ADN）单元推进剂的热分解和燃烧性能的影响。
The effect of organ-metallic compound OME on the combustion and thermal decomposition of ammonium dinitramide (ADN) was investigated by burning rate measurement, DSC and TG.
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。
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.
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。
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.
为了了解塞式喷管性能，采用固体推进剂对塞式喷管单元发动机进行了模拟实验。
To find out the performance characteristic of aerospike nozzle, the simulated tests were a aerospike engine unit using solid propellant.
为了了解塞式喷管性能，采用固体推进剂对塞式喷管单元发动机进行了模拟实验。
To find out the performance characteristic of aerospike nozzle, the simulated tests were a aerospike engine unit using solid propellant.
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