پژوهشگاه فضایی ایران- انجمن هوافضای ایران علوم، فناوری و کاربردهای فضایی 2783-4557 مقالات آماده انتشار 2025 11 08 Preliminary Design and Analysis of a Hall Effect Thruster Employing Scaling Law Methodology Preliminary Design and Analysis of a Hall Effect Thruster Employing Scaling Law Methodology 233804 10.22034/jssta.2025.523511.1250 FA Samira Mir Mazhari Anvar Iranian Space Research Center 0000-0001-7205-2406 Morteza Farhid Space Thrusters Research Institute, Iranian Space Research Center, Tabriz, Iran 0000-0001-7205-2406 Journal Article 2025 05 14 The Hall thruster scaling methodology is an essential framework for the initial design of Hall Effect Thrusters (HETs). This methodology establishes scaling relationships between key performance metrics, such as thrust and specific impulse, and three independent parameters: geometric dimensions, discharge voltage, and the atomic number density of the propellant. This approach serves as a valuable tool for predicting thruster performance with different propellants and discharge voltages during the preliminary design phase. In this study, we propose a modified scaling method that includes formulas for calculating the length, width, and mean diameter of the discharge channel, as well as the maximum magnetic field intensity, based on data from a mid-power reference Hall Effect Thruster (SPT-100). The proposed method was validated through the design of two Hall Effect Thrusters: one low-power model (SPT50) with a power level of approximately 300 W and one high-power model (T220) with a power level of around 10 kW. The simulation results allow for estimating the performance of the xenon-optimized thruster when operated with alternative propellants, such as krypton. These results show that the performance of the thruster can be improved by slightly increasing the discharge voltage while maintaining a constant propellant mass flow rate. The Hall thruster scaling methodology is an essential framework for the initial design of Hall Effect Thrusters (HETs). This methodology establishes scaling relationships between key performance metrics, such as thrust and specific impulse, and three independent parameters: geometric dimensions, discharge voltage, and the atomic number density of the propellant. This approach serves as a valuable tool for predicting thruster performance with different propellants and discharge voltages during the preliminary design phase. In this study, we propose a modified scaling method that includes formulas for calculating the length, width, and mean diameter of the discharge channel, as well as the maximum magnetic field intensity, based on data from a mid-power reference Hall Effect Thruster (SPT-100). The proposed method was validated through the design of two Hall Effect Thrusters: one low-power model (SPT50) with a power level of approximately 300 W and one high-power model (T220) with a power level of around 10 kW. The simulation results allow for estimating the performance of the xenon-optimized thruster when operated with alternative propellants, such as krypton. These results show that the performance of the thruster can be improved by slightly increasing the discharge voltage while maintaining a constant propellant mass flow rate.