火箭推进2026，Vol.52Issue(3)：113-125,13.DOI:10.3969/j.issn.1672-9374.2026.03.011
磁等离子体发动机磁喷管加速过程的混合模拟
Hybrid simulation for acceleration process of magnetic nozzle in magnetoplasma rocket engine
杨文涛 1杨振宇 1刘志超 1范威 1韩先伟 1谭畅1
作者信息
- 1. 西安航天动力研究所陕西省等离子体物理与应用技术重点实验室,陕西西安 710100
- 折叠
摘要
Abstract
Magnetoplasma rocket engine(MPRE)has many advantages,such as high thrust,high specific impulse,adjustable thrust-to-specific impulse ratio and so on.It has broad application prospects in fields like manned spaceflight and deep space exploration.The momentum transfer and energy conversion process of plasma in the magnetic nozzle is crucial to the thrust generation in the magnetoplasma rocket engine,and the optimized design of the magnetic nozzle is of great significance for enhancing engine performance.In this paper,an axisymmetric fluid-PIC(Particle in cell)hybrid model is used to simulate the ion acceleration process in the magnetic nozzle under the conditions of different magnetic field configurations and magnetic field intensities,inlet ion temperatures and ion number densities.The dominant acceleration mechanism of the magnetic nozzle is studied,and the effects of various factors on the performance of the magnetic nozzle are analyzed.The results show that the magnetic field configuration,magnetic field strength,and the inlet ion temperature have an important effect on the ion acceleration process and engine propulsion performance in the magnetic nozzle.The inlet ion number density significantly affects the engine thrust,but has little effect on the efficiency and specific impulse of the magnetic nozzle.Among the three mechanisms of Hall acceleration,electrostatic field acceleration and gas dynamic acceleration,the Hall acceleration mechanism plays a leading role in the upstream of the magnetic nozzle,and the gas dynamic effect plays a leading role in the downstream.The change of the above-mentioned factors will affect the position of the department point between the ion and the magnetic field in the magnetic nozzle,thus affecting the acceleration process of the ion in the magnetic nozzle.关键词
磁等离子体发动机/磁喷管/加速机制/混合模拟Key words
magnetoplasma rocket engine/magnetic nozzle/acceleration mechanism/hybrid simulation分类
航空航天引用本文复制引用
杨文涛,杨振宇,刘志超,范威,韩先伟,谭畅..磁等离子体发动机磁喷管加速过程的混合模拟[J].火箭推进,2026,52(3):113-125,13.
