| 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。 |
| 关键词: 姿控发动机 喷雾试验 高空模拟试验 |
| DOI： |
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| 基金项目: |
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| Investigation on Performance of Small-Thrust Bi-Propellant Thruster for Attitude Control |
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MAO Xiao-fang1,2, WANG Feng-shan2, YANG Xiao-hong2, CAI Guo-biao1
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1.School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;2.Beijing Institute of Control Engineering, Beijing 100190, China
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| Abstract: |
| To investigate the performance of a new small-thrust bi-propellant thruster, experiments were conducted on the discharge device with two-dimensional particle dynamic analyzer, as well as with the 42km-high-altitude simulation test facility. The results show that the nominal specific impulse of the thruster is increased to 290s, and the minimum impulse is reduced to 50mN·s, which indicates the significant improvement of the new thruster performance and the consequent satisfaction of the high performance demand for the satellite as well as the capacity for replacing current 10N thruster for attitude control. |
| Key words: Attitude control thruster Discharge experiment High-altitude simulation experiment |
