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New discrimination method for ablative control mechanism in solid-propellant rocket nozzle

Science china(Technological Sciences) 2010年第10期53卷 2718-2724页

作者： zhang bin, liu yu, wang changhui & ren junxue school of astronautics, beijing university of aeronautics and astronautics, beijing 100083, china school of astronautics Beijing University of Aeronautics and Astronautics Beijing China

A reasonable discrimination method for ablative control mechanism in solid-propellant rocket nozzle can improve the calculation accuracy of ablation rate. Based on the different rate constants for reactions of C with H2O and CO2,a new discrimination method for ablative control mechanism,which comprehensively considers the influence of nozzle surface temperature and gas component concentration,is presented. Using this new discrimination method,calculations were performed to simulate the nozzle throat insert ablation. The numerical results showed that the calculated ablation rate,which was more close to the measured values,was less than the value calculated by diffusion control mechanisms or by double control mechanisms. And H2O was proved to be the most detrimental oxidizing species in nozzle ablation.

关键词： nozzle Ablation diffusion control mechanism chemical kinetics control mechanism discrimination method

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Coupling plasma plume of a low-power magnetically shielded Hall thruster with a hollow cathode

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Chinese Journal of aeronautics 2020年第12期33卷 3018-3026页

作者： Guangchuan zhang junxue ren Wei LIANG Ning OUYANG Chao LU Haibin TANG school of Space and Environment Beihang UniversityBeijing 100083China school of astronautics Beihang UniversityBeijing 100083China Shanghai Institute of Space Propulsion Shanghai 201112China Key Laboratory of Spacecraft Design Optimization&Dynamic Simulation Technologies Ministry of EducationBeijing 100083China Laboratory of Space Environment Monitoring and Information Processing Ministry of Industry and Information TechnologyBeijing 100083China

The coupling region of a Hall thruster with a hollow cathode is the region between the cathode and the thruster *** characteristics of plasma in that region are complicated and strongly associated with the thruster working conditions and the cathode *** this paper,a laboratory 100 W class magnetically shielded Hall thruster was coupled with a hollow *** imaging and electrostatic probe were employed to monitor and scan the plasma *** characteristics in the coupling region in non-self-sustained mode and self-sustained mode were *** of the coupling plume with the cathode position was *** show that,when turning the thruster into self-sustained mode or moving the cathode further away axially,the discharge current can be reduced by 6.4–10.6%restraining the electron current and improving *** particular,when the cathode is moved further,the electron conduction near the channel walls is *** electron current is reduced by 27.4%and the ion beam current is increased by 7%.Overall,this work shows that the working mode of the thruster and the position of the cathode greatly affect the coupling plasma *** play an important role in improving the utilizations of propellant and current.

关键词： Coupling region Electron conduction Hall thruster Hollow cathode Utilizations of propellant and current

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