甲烷/氧气双组元微型推力室的实验研究

为研究微小推力室的工作特点,建立了双组元微小推力室的地面实验装置和数据采集系统。在内径为4mm,喉部直径为0.4mm的微小推力室内,采用氧气和甲烷气体作为推进剂进行了点火热试车,实时测量燃烧室压力和壁面的温度分布。实验结果表明,在富燃工况下,随着混合比的升高,燃烧温度和燃烧室压力逐渐升高;当混合比一定时,随着总流量的增加,燃烧室压力增加,微小推力室的推力和比冲也在升高。微小推力室的真空推力达到120mN,真空比冲达到了240s。

Experimental study on methane-oxygen bipropellant micro-thruster

To understand characteristics of micro-thruster, ground-experimental apparatus of bipropellant micro-thruster and data acquisition system were established. A micro-thruster with inner diameter of 4mm and throat diameter of 0.4mm was manufactured. Hot-fire tests in this micro-thruster at different O/F and chamber pressure were conducted by using methane and oxygen as propellants. Chamber pressure and outside wall temperatures of the micro-thruster were measured. Test results show that under fuel-rich conditions, combustion temperature and chamber pressure increase with the increasing of O/F. When O/F is fixed, chamber pressure increases with total flow rate increasing and vacuum thrust of the micro-thruster also increases. The maximum vacuum thrust is 120mN and the maximum vacuum specific impulse reaches 240s.