An atmosphere-breathing electric propulsion system (ABEP) uses the rarefied atmospheric molecules as the propellant for the electric thruster. In the best case, it can allow spacecraft (S/C) complete a long-time mission in very low Earth orbit (VLEO) without carrying any propellant. However, previous studies have shown that the thruster lifetime is limited by electrode erosion due to the aggressive gases, such as the atomic oxygen in VLEO. This paper design and analyse an inductively coupled plasma generator (ICPG) for ABEP system, and it is electrodeless to avoid electrode erosion. Based on the COMSOL Multiphysics, the simulation model of ICPG is established and analyzed. Multiple physical fields are coupled in this model including plasma, magnetic field, and flow field. The simulation model is verified by the experimental results of the literature. Driving by the radio frequency power, the plasma power distribution and thrust estimation of the ICPG under different input conditions (different drive powers and different operation gases) can be obtained. The results show that the ICPG may have a better performance under the condition of low mass flow and high drive power to compensate the drag. The gas species and their proportions have also great influence on the behaviours of ICPG. This paper can provide a convenient and efficient method to study the ICPG products for ABEP.

吸气式电力推进系统 (ABEP) 使用稀薄的大气分子作为电动推进器的推进剂。在最好的情况下，它可以让航天器（S/C）在不携带任何推进剂的情况下完成超低地球轨道（VLEO）的长期任务。然而，先前的研究表明，推进器的寿命受到电极侵蚀的限制，这是由于腐蚀性气体，例如 VLEO 中的原子氧。本文设计并分析了一种用于ABEP系统的电感耦合等离子体发生器（ICPG），它是无电极的以避免电极腐蚀。基于COMSOL Multiphysics，建立并分析了ICPG的仿真模型。该模型中耦合了多个物理场，包括等离子体、磁场和流场。仿真模型得到了文献实验结果的验证。通过射频功率驱动，可以获得ICPG在不同输入条件下（不同驱动功率和不同操作气体）的等离子体功率分布和推力估计。结果表明，ICPG在低质量流量和高驱动功率条件下可能具有更好的补偿阻力性能。气体种类及其比例对ICPG的行为也有很大影响。本文可为研究ABEP的ICPG产物提供一种方便、有效的方法。结果表明，ICPG在低质量流量和高驱动功率条件下可能具有更好的补偿阻力性能。气体种类及其比例对ICPG的行为也有很大影响。本文可为研究ABEP的ICPG产物提供一种方便、有效的方法。结果表明，ICPG在低质量流量和高驱动功率条件下可能具有更好的补偿阻力性能。气体种类及其比例对ICPG的行为也有很大影响。本文可为研究ABEP的ICPG产物提供一种方便、有效的方法。