Understanding of Physical Phenomena for Development of Electric Propulsion Systems

为了了解等离子体加速过程、放电特性、羽流特性以及航天器与等离子体羽流相互作用等物理现象，为电推进系统的研制提供依据，在推力测量的基础上，还进行了等离子体诊断测量和数值模拟。作为电推进系统，磁等离子体动力（MPD）推力器，电弧喷射推力器与150 mN，射频离子推力器，微波离子推力器和霍尔推力器进行了研究。此外，进行了使命分析，并开发了小推力轨道优化程序的电力推进。在其他领域进行了研究，如C60离子推进剂的可行性，和离子推进器的碳-碳网格。得到了300 W和1 kW电弧喷射发动机的基本推力性能，并采用双流体热非平衡模型对其流场进行了分析。研究了磁场对磁等离子体推力器推力特性的影响。霍尔推力器的推力性能也被测量为不同的加速通道长度。

In order to understand physical phenomena, such as plasma acceleration processes, discharge features, plume features and spacecraft and plasma plume interaction, for development of electric propulsion systems, plasma diagnostic measurement and numerical simulation were made in addition to thrust measurement. As electric propulsion systems, magnetoplasmadynamic (MPD) thrusters, arcjet thrusters with 150 mN,RF ion thrusters, microwave ion thrusters and Hall thrusters were investigated. Furthermore, mission analysis was conducted, and low-thrust trajectory optimization codes were developed for electric propulsion. Studies were carried out in other fields such as feasibility of C60 for ion thruster propellant, and carbon-carbon grids for ion thrusters. Fundamental thrust performances for 300W and 1kW arcjet thrusters were obtained, and the flowfields were analyzed using a two-fluids thermal-nonequilibrium model. In MPD thrusters, the effects of applied magnetic fields on the thrust characteristics were studied. The thrust performance for Hall thrusters was also measured varying acceleration channel length.