物理学报2018，Vol.67Issue(4)：1-13,13.DOI:10.7498/aps.67.20171972
超声波电喷推力器羽流中和特性研究
Plume neutralization mechanism for ultrasonically aided electrospray thruster
于博 1张岩 2贺伟国 2杭观荣 3康小录 2赵青2
作者信息
- 1. 电子科技大学物理电子学院,成都 611731
- 2. 上海空间推进研究所电推进事业部,上海 201112
- 3. 上海交通大学机械与动力工程学院,上海 200240
- 折叠
摘要
Abstract
The ultrasonically aided electrospray thrusters (UAET) are used mainly on micro-satellites (with mass less than 10 kg). In this work, numerical simulation studies of the UAET plume field are conducted to investigate the following two problems encountered during operational tests: the avertence angle of thrust direction, which exists between the design and test outcome, and the lower energy efficiency than the established theoretical value. In order to precisely model the special physical process of the UAET plume neutralization, we develop a new hybrid model named the neutralization of electrons and charged droplets for the plume fluid field to capture the neutralization process of electrons and positively charged droplets. This model describes the dynamical movement of particles, the collision between electrons and droplets, the breakage and coalescence of the droplets, and the flow and heat transfer between the droplets and background gas. To show the feasibility and accuracy of the model, experimental tests involving thrust measurements and high-speed photography of the plume are conducted. The comparison between the test and simulation results under the same study conditions shows that the average error of this model is about 20%, and both the test and calculation exhibit a consistent trend in the various study cases. According to this model, we simulate the plume fluid field of UAET (with 2-W discharge power and 2-mA current) and identify the distribution characteristics of several parameters, including the droplet number density, charge density and the droplet volume, as well as the energy consumption categories that occur. Our model can successfully demonstrate the internal mechanisms that cause the two problems identified above. Our work will provide support for future studies of optimal design.关键词
超声波电喷推力器/带电液滴中和模型/羽流中和特性/数值模拟Key words
ultrasonically aided electrospray thruster/neutralization model of electrons and charged droplets/neutralization characteristics of plume/numerical simulation引用本文复制引用
于博,张岩,贺伟国,杭观荣,康小录,赵青..超声波电喷推力器羽流中和特性研究[J].物理学报,2018,67(4):1-13,13.
