中国空间科学技术（中英文）2025，Vol.45Issue(2)：103-113,11.DOI:10.16708/j.cnki.1000-758X.2025.0028
离子液体电喷推力器仿真及性能优化分析
Simulation and performance optimization analysis of ionic liquid electrospray thruster
摘要
Abstract
As aerospace technology advances,ionic liquid electrospray thrusters(ILET)are gaining attention for their efficiency and stability.This study delves into the performance limits of ILET by simulating the electrospray process,using a coupled electric and flow field approach.Performance parameters are analyzed by using the response surface methodology(RSM),leading to optimal operational and structural parameters.The findings indicate that,with a 20 μm emitter diameter,119.384 μm height,3.45 × 10-2 nL/s flow rate,and 2 188.249 V voltage,the maximum thrust is 1.464μN;with a 48μm diameter,119μm height,1.9 ×10-2 nL/s flow rate,and 2600 V voltage,the highest specific impulse reaches 1077.543 s.The simulation and model results align closely with experimental data,with an error margin within 5％,confirming the model's reliability.Innovatively combining electric and flow field coupling with RSM not only enhances analytical precision,but also opens new avenues for evaluating similar complex systems.Furthermore,this research provides a solid theoretical foundation for ILET's application in aerospace,demonstrating its potential for future space missions.关键词
离子液体/响应面法/性能优化/参数分析/CFDKey words
ionic liquid/response surface methodology/performance optimization/parameter analysis/CFD分类
航空航天引用本文复制引用
潘宁,耿海,郭宁,曲富饶,雪佳强,孟伟,刘坤..离子液体电喷推力器仿真及性能优化分析[J].中国空间科学技术（中英文）,2025,45(2):103-113,11.基金项目
国家重点研发计划引力波探测专项(2021YFC2202704) （2021YFC2202704）
