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Diagnostic and modelling investigation on the ion acceleration and plasma throttling effects in a dualemitter hollow cathode micro-thruster

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Chinese Journal of Aeronautics 2021年第12期34卷 85-98页

作者： Zhongxi NING Chenguang LIU Ximing ZHU Yanfei WANG Bingjian AN Daren YU Plasma Propulsion Laboratory Harbin Institute of TechnologyHarbin 150001China

Hollow cathode discharges are widely used as neutralizers for the electric propulsion systems and recently developed into micro-thrusters for the small satellites.In this work,a dualemitter hollow cathode thruster is developed,which can be operated in two different modes—the neutralizer mode and the micro-thruster mode.For characterizing this kind of new device,the Langmuir probe,Faraday probe,and retarding potential analyzer are used to determine the electron temperature,electron density,ion flux,and ion energy distribution function.The operating parameters,including the thrust,and specific impulse,are also measured.A two-dimensional self-consistent extended fluid model is employed to calculate the spatial distribution of plasma parameters and the fluid field of electrons in the region around the emitters.By comparing the diagnostic and modelling results,it is found that the change in the electric field and ionization zone is the essential reason for the different performances of the device in the neutralizer and micro-thruster modes.Variation in the electric field leads to an ion acceleration effect in the micro-thruster mode;moving of the ionization zone raises the plasma pressure in the orifice region of the hollow cathode,and thus leads to enhanced plasma throttling and gas expanding effects.By analyzing the above mechanisms,the possible methods for improving this kind of hollow cathode micro-thruster are discussed.

关键词： Extended fluid model Hollow cathodes micro-thruster Plasma contactor Plasma throttling effect

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A Status Graph Based Control Allocation Algorithm of Digital micro-thruster Array for micro/Nano-Satellites Orbit Control Application

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Transactions of Nanjing University of Aeronautics and Astronautics 2019年第5期36卷 779-788页

作者： ZHANG Dandan ZHANG Yunyi DONG Ke LI Haiwang WANG Shaoping School of Energy and Power Engineering Beihang UniversityBeijing 100191P.R.China School of Automation Science and Electrical Engineering Beihang UniversityBeijing 100191P.R.China

Digital micro-thruster arrays can be used for special missions of micro/nano-satellites with the requirements of high precision and small impulse.This paper presents a novel control allocation algorithm for the digital micro-thruster array,namely status graph based control allocation(SGBCA)algorithm,which aims at finding the optimal micro thrusters combination scheme to realize the sequential control synthesis for micro/nano-satellite during real-time orbit control tasks.A mathematical model is set up for the control allocation of this multivariate over-actuated system.Through dividing thrusters into disjoint segments by offline calculation and combining segments dynamically online to provide a sequence of the required impulse for the micro/nano-satellite,the time complexity of the control allocation algorithm decreases significantly.All levels of impulse can be generated by the digital micro thruster arrays and the service life of the arrays can be extended using the segment converting strategy proposed in this paper.The simulation indicates that the algorithm can satisfy the requirements of real-time orbit control for micro/nano-satellites.

关键词： control allocation digital micro-thruster array micro/nano-satellite orbit control

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Effect of Pressure Level on the Performance of an Auto-Initiated Pulsed Plasma thruster

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Plasma Science and Technology 2010年第4期12卷 466-472页

作者： Kelvin LOH Abhijit KUSHARI Department of Aerospace Engineering Nanyang Technological University Department of Aerospace Engineering Indian Institute of Technology

Pulsed plasma thrusters （PPT） are micro-propulsion devices used in satellites for station keeping. Conventionally the plasma discharge in a PPT is initiated by a spark plug. The primary objective of the present work was to develop and characterize a PPT that does not need a spark plug to initiate the plasma discharge. If the spark plug is eliminated, the size of the thrusters can be reduced and arrays of such thrusters can be manufactured using micro electro mechanical systems （MEMS） techniques, which can provide tremendous control authority over the satellite positioning. A parallel rail thruster was built and its performances were characterized inside a vacuum chamber to elucidate the effect of vacuum level on the performance. The electrical performance of the thruster was quantified by measuring the voltage output from a Rogowski coil, and the thrust produced by the developed thruster was estimated by measuring the force exerted by the plume on a light weight pendulum, whose deflection was measured using a laser displacement sensor. It was observed that the thruster can operate without a spark plug. In general, the performance parameters such as thrust, mass ablation, impulse bit, and specific impulse per discharge, would increase with the increase in pressure up to an optimum level due to the increase in discharge energy as well as the decrease in the total impedance of the plasma discharge. The thrust efficiency is found to be affected by the discharge energy.

关键词： plasma thruster auto-initiation solid propellant micro-thruster

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