An integrative mathematical model of microwave ion thruster for mHz-frequency thrust noise analysis
作者机构：Plasma Propulsion LaboratoryHarbin Institute of TechnologyHarbin 150001China
出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)
年 卷 期：2024年第37卷第4期
页 面：121-136页
核心收录：
学科分类：080703[工学-动力机械及工程] 082502[工学-航空宇航推进理论与工程] 08[工学] 0807[工学-动力工程及工程热物理] 0825[工学-航空宇航科学与技术]
基 金：the National Key R&D Program of China (No. 2020YFC22 01000) the National Natural Science Foundation of China (No. 11927812)
主 题：Electric propulsion Microwave ion thruster Integrative model Sheath property Ion beamlet divergence Thrust noise Plasma
摘 要：Many high-precision space missions need thrusters to produce thrust with low noise to compensate for disturbances and ensure satellite platform stability. Microwave ion thruster is characterized with a wide thrust range and potential for these missions. A cost-effective and accurate mathematical model is crucial for mHz-frequency thrust noise analysis and feedback controller design. The Particle-In-Cell(PIC) and global models are two common simulation tools. The PIC model is characterized with high accuracy but huge computation cost, which is difficult to analyze long-time performance characteristics. Now, the global model is only used for the discharge chamber with low accuracy and cannot reflect ion extraction properties. In this paper, an integrative mathematical model is built for a 1-cm microwave ion thruster and can reflect ion beamlet divergence and impingement on the Accelerator Grid(AG). Simulation results show good agreement with experiments at 0.06 sccm. However, the model demonstrates worse consistency with experiments when the flux increases to 0.1 sccm, which may be because the influence of neutral gas on the Electron Cyclotron Resonance(ECR) is not considered in the model. A long-time(1000 s) simulation is conducted with this model under 35 μN. It takes 3 hrs, and the thrust noise reaches 1 μN/Hz^(0.5) at 1 mHz.
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