磁等离子体发动机磁喷管加速过程的混合模拟OA

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.