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离子推力器工作产生的羽流会对航天器产生影响,严重时甚至会造成航天器无法正常工作,为了精确评估离子推力器羽流特性及其对航天器的作用,采用基于粒子轨道理论(PIC,Particle-In-Cell)的模型对复杂的航天器的离子推力器羽流进行了数值模拟,并结合最近几年发展起来的浸入式有限元(IFE,Immersed Finite Ele-ment),采用结构网格准确计算复杂边界电场。通过模拟,获得了Mo+CEX离子在卫星表面的最大可能沉积分布,定量分析了卫星表面Mo+CEX离子的最大可能沉积率,表明在垂直于推力器主束流方向的卫星组件的表面上容易产生较大的Mo+CEX离子污染沉积率,而平行于推力器主束流方向上Mo+CEX离子污染沉积率相对较小。
The plume generated by the operation of the ion thruster will affect the spacecraft and may even cause the spacecraft to work abnormally. In order to accurately evaluate the plume performance of the ion thruster and its effect on the spacecraft, the particle trajectory theory (PIC (Particle-In-Cell) model is used to simulate the ion thruster plume of complex spacecraft. Combined with Immersed Finite Element (IFE) developed in recent years, Accurate Computation of Complex Boundary Electric Field. Through simulation, the maximum possible depositional distribution of Mo + CEX ions on the satellite surface was obtained, and the maximum possible deposition rate of Mo + CEX ions on the satellite surface was quantitatively analyzed, indicating that the surface of the satellite assembly perpendicular to the main beam direction of the thruster is easy The deposition rate of Mo + CEX ions is larger, while the deposition rate of Mo + CEX ions parallel to the main beam of the thruster is relatively smaller.