Investigation of low discharge voltage Hall thruster characteristics and evaluation of loss mechanisms
Investigation of low discharge voltage Hall thruster characteristics and evaluation of loss mechanisms
复制标题
低放电电压霍尔推进器特性研究及损耗机制评估
DOI：
--
复制
发表时间：
2009
期刊：
影响因子：
--
通讯作者：
Daniel L. Brown
中科院分区：
文献类型：
--
作者：
Daniel L. Brown
摘要：在霍尔推进器技术的早期发展阶段，等离子体研究和推进进步主要集中在 300 V、1600 s 比冲运行。自 1972 年第一台推进器在苏联卫星上发射以来，对等离子动力放电现象和运行特性的广泛研究使推进概念发展到了适合各种近地机动和行星际任务的高水平性能。性能范围的扩大主要是推进器寿命、热裕度、放电稳定性和电力系统能力改进的结果。霍尔推进器推进系统的进步使得推进器的输入参数范围更广，包括所施加的阳极电位。低放电电压状态下的操作与总推进器效率的下降相关。本论文旨在研究低压霍尔推进器物理学，确定主要的性能损失机制，并确定提高效率的放电特性。
Abstract : During the early development stages of Hall thruster technology, plasma research and propulsion advancements centered primarily on 300 V, 1600 s specific impulse operation. Since the first thruster firing on a Soviet satellite in 1972, extensive investigations of the plasmadynamic discharge phenomena and operating characteristics progressed the propulsion concept to a high-level of performance suitable for a wide range of near-earth maneuvers and interplanetary missions. The expanded performance envelope is primarily a function of improvements in thruster lifetime, thermal margin, discharge stability, and power system capability. Advancements in the Hall thruster propulsion system have enabled a wider range of input parameters to the thruster, including the applied anode potential. Operation in the low discharge voltage regime is associated with a decline in total thruster efficiency. This dissertation is intended to investigate low voltage Hall thruster physics, identify dominant performance loss mechanisms, and determine the discharge characteristics that drive efficiency.