Experimental Investigation of a Monopropellant Thruster Using Nitrous Oxide
Experimental Investigation of a Monopropellant Thruster Using Nitrous Oxide
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使用一氧化二氮的单组元推进剂推进器的实验研究
DOI：
10.5028/jatm.v6i4.382
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发表时间：
2014
影响因子：
--
通讯作者：
F. Costa
中科院分区：
文献类型：
--
作者：
L. Hennemann;J. C. Andrade;F. Costa
一氧化二氮是一种单元推进剂，有可能用于卫星轨道修正、定位和姿态控制的推进系统。本文介绍了实验结果与2N推力器原型采用一氧化二氮气体分解的氧化铑催化剂负载在氧化铝上。首先，推力器的设计，测试台架和测试程序进行了说明。然后给出了脉冲工作时推力曲线、质量流量、推力器沿着压力和温度的主要实验结果。在比冲结束时，确定了特征速度和推进器效率，从而表明催化分解效率约为88%。
Nitrous oxide is a monopropellant with potential for use in propulsion systems for orbit correction, positioning and attitude control of satellites. This paper presents experimental results with a 2N thruster prototype employing nitrous oxide gas decomposed by a rhodium oxide catalyst supported on alumina. Initially, the thruster design, the test bench and test procedures are described. Then the main experimental results, including thrust curves, mass flow rates, pressures and temperatures along the thruster are presented for pulsed operation. At the end specific impulses, characteristic velocities and thruster efficiencies are determined, thus indicating a catalytic decomposition efficiency of about 88%.