面向精确姿态控制和轨道调整的空间探测任务对航天器推进系统提出微推力、高精度、宽范围连续可调的要求。会切型霍尔推力器具有结构简单、推力范围大、推功比高和寿命长的特点，提出一种通道更窄，磁场更强的μN级会切型霍尔推力器。在微流量条件下，较窄的通道增大了放电室内推进剂的密度，较强的磁场提高电子的约束效率，促进了电子与推进剂原子的碰撞电离过程，容易实现推进器稳定的推力输出。实验结果表明，选用推进剂Xe，工况为流量范围0.5~1.0 sccm，电压范围0~300 V，实现推力输出范围5.4~518.9 μN，响应时间优于150 ms，推力噪声在0.05~1 Hz频段达到0.1 μN/Hz1/2。当推进剂Xe流量为0.5 sccm，电压为500 V时，推力输出达到50 μN，比冲达到104 s。通过优化磁场设计等，μN级会切型霍尔推力器性能可以进一步提升，有望满足空间探测任务需要。
王豪
,
穆建超
,
丛麟骁
,
李英民
,
刘捷
,
乔从丰
. μN级推力器设计与实验研究[J]. 中国科学院大学学报, 2025
, 42(3)
: 412
-420
.
DOI: 10.7523/j.ucas.2023.058
The space exploration missions for precise attitude control and orbit adjustment require spacecraft propulsion systems with micro-thrust, high precision, and wide-range continuous adjustment. The cusp-type Hall thruster has the characteristics of simple structure, large thrust range, low power consumption and long working life. This paper proposes a micro-newton cusp Hall thruster with narrower channel and stronger magnetic field. Under micro-flow rate conditions, the narrower channel increases the density of the propellant in the discharge chamber, and the stronger magnetic field improves the confinement efficiency of electrons. This promotes the collision ionization process between electrons and propellant atoms, and the stable thrust of the thruster output is realized. The experimental results show that the flow range(propellant is Xe) is 0.5-1.0 sccm, the voltage range is 0-300 V, the thrust range reaches 5.4-518.9 μN. The response time is better than 150 ms, and the thrust noise reaches 0.1 μN/Hz1/2 at 0.05-1 Hz. When the flow rate of propellant Xe is 0.5 sccm and the voltage is 500 V, the thrust output reaches 50 μN and the specific impulse reaches 104 s. By optimizing the magnetic field design, the performance of this type of micro-newton cusp Hall thruster can be further improved, which can meet the requirements of space exploration missions.
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