| Investigation into the transient flow characteristics of noble gas propellants using the pulsed inductive discharge in electric propulsion |
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| 作者姓名： | Yuguo CHENG Guangqing XIA |
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| 作者单位： | 1. PLA 91550 Element 41;2. State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian University of Technology;3. Key Laboratory of Advanced Technology for Aerospace Vehicles of Liaoning Province, Dalian University of Technology |
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| 基金项目： | supported by the National Natural Science Foundation of China (Nos. 11675040 and 11702319)； |
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| 摘 要： | The Pulsed Inductive Thruster(PIT) has the advantages of repeatable startup, no corruption and in-situ propellant feed. To study the flow expansion and circuit characteristics of PITs,the circuit-fluid model is developed, and the high temperature thermodynamic and transport models are combined with the circuit-fluid model to predict the critical plasma parameters. The flow fields of initial mass of 2–8 mg and charge voltages of 10–14 k V are simulated. Comparison of the flow fields of argon and ...
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| 收稿时间： | 1 August 2019 |
Investigation into the transient flow characteristics of noble gas propellants using the pulsed inductive discharge in electric propulsion |
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| Yuguo CHENG,Guangqing XIA.Investigation into the transient flow characteristics of noble gas propellants using the pulsed inductive discharge in electric propulsion[J].Chinese Journal of Aeronautics,2020,33(9):2329-2341. |
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| Institution: | 1. PLA 91550 Element 41, Dalian 116023, China;2. State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian University of Technology, Dalian 116024, China;3. Key Laboratory of Advanced Technology for Aerospace Vehicles of Liaoning Province, Dalian University of Technology, Dalian 116024, China |
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| Abstract: | The Pulsed Inductive Thruster (PIT) has the advantages of repeatable startup, no corruption and in-situ propellant feed. To study the flow expansion and circuit characteristics of PITs, the circuit-fluid model is developed, and the high temperature thermodynamic and transport models are combined with the circuit-fluid model to predict the critical plasma parameters. The flow fields of initial mass of 2–8 mg and charge voltages of 10–14 kV are simulated. Comparison of the flow fields of argon and helium propellants suggests that, the flow field structures are similar. Slight differences exist on the magnitude of the density and magnetic field, caused by larger velocity in lighter atom case and difference on the ionization gap between adjacent ionization levels. Analysis of the circuit characteristics by the two-dimensional results indicates that the ratio of coil inductance to circuit inductance affects both the rise rate and phase of the plasma current, the larger the ratio, the greater the rise rate and the better the following characteristic. The calculations show that the magnetic energy obtained within the decoupling distance determines the overall performance the thruster can be obtained; self-induced field maintained by the thermal motion after the main pulse leads to the long attenuation process and difference on the total impulse when the angle of conical pylon is varied under constant coil dimension. |
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| Keywords: | Argon and helium propellants Circuit characteristics Circuit-fluid model Flow properties Pulsed inductive thruster |
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