电推进羽流诊断系统探针组件研制及应用验证

Development and Verification of Probe Assembly for Electric Propulsion Plume Diagnostic System

为了满足电推进产品研制过程中对产品性能可靠性评价及电推进羽流与航天器相互作用分析的需求,研制了集法拉第探针、阻滞势分析仪、朗缪尔探针、电源处理单元以及测控软件为一体的电推进羽流诊断系统。在LIPS200离子电推进上的性能验证试验表明,所有探针能够获取典型的特征曲线和诊断结果。FP在距推力器出口平面150 mm处测量的离子电流密度在0.02~0.80 mA/cm^(2),密度在0.66~0.80 mA/cm^(2)的主离子束直径为90 mm。柱形LP和平面LP在距推力器出口500 mm处测量等离子体电子温度分别为1.3 eV和1.2 eV,电子密度分别为2.1×10^(15) m^(-3)和2.0×10^(15) m^(-3);等离子电位均为4.6 V。RPA在距推力器出口500 mm处测量的单位电荷离子能量为1001 eV±44 eV(k=2),而LIPS200的总加速电压为1185 V,表明测量结果正确。

In order to satisfy the requirements of the reliability evaluation during the electric propulsion being developed and the interaction analysis between electric propulsion and spacecraft,an electric propulsion plume diagnostic system integrated Faraday probe and Langmuir probe and Retarding potential analyzer with power processing unit and measurement and control software was developed.The performance verification test demonstrated with LIPS200 ion thruster show that the typical characteristic curve and diagnostic results can be obtained with all probe.The ion current density measured with FP at 150 mm from exit plane of the thruster ranges from 0.02 mA/cm^(2) to 0.80 mA/cm^(2),and the main ion beam diameter with the density between 0.66 mA/cm^(2) and 0.80 mA/cm^(2) is 90 mm.The plasma parameters measured with the cylindrical LP and the planer LP at 500 mm from exit plane of the thruster show that the electron temperatures are respectively 1.3 eV and 1.2 eV,and the electron densities are respectively 2.1×10^(15) m^(-3)and 2.010^(15) m^(-3),and the plasma potentials are same value of 4.6 V.Ion energy-per-charge measured with RPA at 500mm from exit plane of the thruster is 1001 eV±44 eV,which is correct by comparing with 1185 V of total accelerating voltage of LIPS200.