Understanding of Physical Phenomena for Development of Electric Propulsion Systems

为了了解等离子体加速过程、放电特征、羽流特征以及航天器与等离子体羽流相互作用等物理现象，为了电力推进系统的发展，除了推力测量外，还进行了等离子体诊断测量和数值模拟。作为电力推进系统，研究了磁等离子体动力（MPD）推进器、150 mN电弧推进器、射频离子推进器、微波离子推进器和霍尔推进器。在此基础上，进行了任务分析，开发了电力推进低推力弹道优化代码。在离子推力器推进剂C60的可行性、离子推力器碳-碳栅格的可行性等方面进行了研究。分别获得了300W和1kW电弧推力器的基本推力特性，并采用双流体热平衡模型对其流场进行了分析。在MPD推力器中，研究了外加磁场对推力特性的影响。对霍尔推力器的推力性能进行了不同加速度通道长度的测量。

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.