标题： 卫星本体对纳米卫星磁等离子体轨道控制的影响 显示英文标题

标题： Effects of Satellite Body on Magnetic Plasma Orbit Control for Nanosatellites

摘要： 磁等离子体轨道控制（MPOC）已被提出用于低地球轨道（LEO）中的太阳同步轨道（SSO）上的微小和纳米卫星。 该方法利用了空间等离子体与磁力矩器（MTQs）周围的磁场相互作用所产生的等离子体阻力。 在本研究中，通过基于全动能模型的等离子体流模拟，研究了有限卫星本体对高电位区域生成的影响。 模拟结果表明，由于停滞在卫星前部的正离子的正电荷被吸收到了卫星表面，因此预测的高电位区域会因有限的卫星本体而缩小。 此外，仅仅在前表面施加偏置电压并不能有效扩展高电位区域。 具体而言，在前表面施加正偏置导致卫星舱内电子的积累，根据施加的电压，卫星的浮动电位会下降。 显示英文摘要

摘要： The magnetic plasma orbit control (MPOC) has been proposed for micro and nanosatellites in the sun-synchronous orbits (SSO) in the low earth orbit (LEO). This method utilizes the plasma drag force generated by the interaction between space plasma and the magnetic field surrounding magnetic torquers (MTQs). In this study, the effects of a finite satellite body on high-potential area generation are investigated by using a plasma flow simulation based on the fully kinetic model. The simulation results show that the predicted high-potential region shrinks due to the finite satellite body because the positive charges of stagnated ions in front of the satellite are absorbed into the satellite surface. In addition, simply applying a bias voltage at the front surface is ineffective in expanding the high-potential region. Specifically, applying a positive bias at the front surface resulted in the accumulation of electrons within the satellite enclosure, causing the floating potential of the satellite to drop according to the applied voltage.