小推力双组元姿控发动机性能研究  

Investigation on Performance of Small-Thrust Bi-Propellant Thruster for Attitude Control

作　　者：毛晓芳[1,2] 汪凤山[2] 杨晓红[2] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]北京控制工程研究所,北京100190

出　　处：《推进技术》2012年第6期987-990,共4页Journal of Propulsion Technology

摘　　要：为了获得新一代小推力双组元姿控发动机的性能,通过采用二维激光粒子动态分析仪的雾化试验台和42km高空模拟试验台,对姿控发动机进行了试验研究。结果表明,在额定工况下,新一代姿控发动机的比冲提高到290s,最小脉冲冲量降低到50mN.s,性能得到了很大改善,可以满足卫星对姿控发动机的性能需求,具备了替代我国现有10N姿控发动机的能力。To investigate the performance of a new small-thrust hi-propellant thruster, experiments were conducted on the discharge device with two-dimensional particle dynamic analyzer, as well as with the 42kin-high-altitude simulation test facili- ty. The results show that the nominal specific impulse of the thruster is increased to 290s, and the minimum impulse is re- duced to 50mN · s, which indicates the significant improvement of the new thruster performance and the consequent satisfac- tion of the high performance demand for the satellite as well as the capacity for replacing current 10N thruster for attitude con- trol.

关 键 词：姿控发动机 喷雾试验 高空模拟试验 

分 类 号：V439.7[航空宇航科学与技术—航空宇航推进理论与工程]