Numerical Simulation of High Specific Impulse Ion Thruster Grid System
نویسندگان
چکیده
منابع مشابه
Numerical Simulation of High Specific Impulse Ion Thruster Optics
A high specific impulse ion thruster (HiIsp-IT) operated at a voltage of 10 kV has been studied and the problems of direct ion impingement on the accelerating grid and of production and impingement of charge-exchange ions have been considered. In order to investigate these problems and to facilitate the design of HiIsp-IT grid systems, a three-dimensional particle simulation code (“igx”) that e...
متن کاملEfficiency Analysis of a High-Specific Impulse Hall Thruster
Performance and plasma measurements of the high-specific impulse NASA-173Mv2 Hall thruster were analyzed using a phenomenological performance model that accounts for a partially-ionized plasma containing multiply-charged ions. Between discharge voltages of 300-900 V, the results showed that although the net decrease of efficiency due to multiplycharged ions was only 1.5-3.0%, the effects of mul...
متن کاملHybrid-PIC modeling of a high-voltage, high-specific-impulse Hall thruster
The primary life-limiting mechanism of Hall thrusters is the sputter erosion of the discharge channel walls by high-energy propellant ions. Because of the difficulty involved in characterizing this erosion experimentally, many past efforts have focused on numerical modeling to predict erosion rates and thruster lifespan, but those analyses were limited to Hall thrusters operating in the 200–400...
متن کاملIon Thruster Grid Lifetime Assessment Based on Its Structural Failure
This article developed an ion thruster optic system sputter erosion depth numerical 3D model by IFE-PIC (Immersed Finite Element-Particle-in-Cell) and Mont Carlo method, and calculated the downstream surface sputter erosion rate of accelerator grid; compared with LIPS-200 life test data. The results of the numerical model are in reasonable agreement with the measured data. Finally, we predicted...
متن کاملNumerical Simulation of the Cathode Plume of a Hall Thruster
The plasma plume generated by the cathode of a 6-kW laboratory Hall thruster is modeled using a hybrid particle-fluid method. The approach utilizes the direct simulation Monte Carlo method to simulate the collision dynamics of heavy particles, the particle-in-cell method to model the transport of heavy species including the effects of electrostatic fields on the ions, and a “fluid” method that ...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: SPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
سال: 2003
ISSN: 1347-3832
DOI: 10.2322/stj.2.1