为促进对纯离子模式下电喷雾推力器的深入理解，分析了电喷雾推力器单发射点受力、供液及离子蒸发行为，建立了发射电流理论模型，明确了电压、供液装置流阻等参数对发射电流的影响规律。所得结果与现有实验数据吻合良好。基于所得模型，进而对单发射点顶端用于发射离子的凸起结构进行了瑞利稳定性分析，得到了单发射点稳定发射的电流上限，并分析了流阻对电流上限的影响。结果表明：发射电流为外加电压的二次函数，与供液装置的流阻成反比关系；纯离子模式存在一个稳定发射电流上限，超过此上限，凸起结构便会破碎；流阻越大，发射电流上限越大。

To enable a more comprehensive understanding of electrospray thrusters operating in pure ion mode， a theoretical model of the emitted current of electrospray thrusters was established. This was achieved by analyzing the force and liquid supply balance of a single emission site， while investigating the influence of parameters such as voltage and flow resistance of the liquid supply device on the emitted current. The results obtained exhibit a strong alignment with existing experimental data. The Raleigh stability of the protruding structure of the emission site was further analyzed based on the theoretical model of emitted current. An upper limit of the current for stable emission was determined， and the impact of flow resistance on this upper limit was assessed. The main findings are as follows： the emitted current demonstrates a direct proportionality to the square of the applied voltage and an inverse proportionality to the flow resistance. In pure ion mode， there exists a maximum limit of current for stable emission， beyond which the protruding structure at the tip of the emission site will fail. Additionally， an increase in flow resistance results in a higher upper limit of the emitted current.

V439⁺.4

国家重点研发计划（2021YFE0116000）；国家自然科学基金（12175032；12102082；12275044；12211530449）；中央高校基本科研业务费（DUT22RC（3）078；DUT21GJ206；DUT22QN232）；河北省科技计划（YCYZ202201；216Z1901G；206Z1902G）；河北省科技创新项目（SJMYF2022X18；SJMYF2022X06）；北京控制工程研究所先进空间推进技术实验室和北京市高效能及绿色宇航推进工程技术研究中心开放基金（LabASP-2022-04）。