journal article·2021-12-01Open access

Study on the electrowetting and beam current characteristics of externally wetted ionic liquid electrospray thruster

Senwen Xue, Li Duan, Qi Kang

AIP Advances· Volume 11· Issue 12

Abstract

It is the theoretical basis to analyze the hydrodynamics mechanism of ionic liquid in an electrostatic field to ensure that the ionic liquid electrospray thruster possesses good wettability. Stable and continuous electrowetting emitters are closely related to thrust noise, resolution, and stability. Therefore, it is urgent to explore the law of ionic liquid electrowetting emitters in an electrostatic field to improve the performance of thrusters. The article proposes a new hybrid emitter structure, which consists of a V-blade emitter and a square capillary. It also carries out numerical simulation of emitter electrowetting under normal gravity and atmospheric conditions and emission experiments to explore the process of ionic liquid layer spreading on the external surface of the emitter. The dimensions of the emitter d1, d2, and θ and the physical properties of ionic liquids jointly determine the electrowetting velocity, the threshold of wetting voltage, and the liquid layer thickness. By analyzing the influence of various variables on electrowetting, a complete emitter electrowetting law of ionic liquid electrospray thrusters is summarized, which provides an important basis for the optimization of the emitter structure. Considering the scale of the emitter and bond ≈1, the meniscus in the electrostatic field is mainly affected by gravity, surface tension, viscous force, and electrophoretic force. Accordingly, it is worth noting that electrophoretic force is calculated by the Maxwell stress tensor method that treats ionic liquids as a dielectric to ensure the continuity of the meniscus. Although it can satisfy the electrowetting study at the macroscale, the interaction between anions and cations at the micro-scale is ignored. The numerical simulation results and the experimental results are correlated. It is proved that the method used in this article is accurate enough to simulate electrowetting before the liquid layer breaks up to form ion emission.
Source: crossref · Quality: baseline

Research context

OpenAlex topics: Electrowetting and Microfluidic Technologies · Electrohydrodynamics and Fluid Dynamics · Microfluidic and Capillary Electrophoresis Applications

SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.

Affiliations

Key Laboratory of Microgravity, Institute of Mechanics, Chinese Academy of Sciences , Beijing 100190, People’s Republic of China and , Beijing 100049, People’s Republic of China

School of Engineering Sciences, University of Chinese Academy of Sciences , Beijing 100190, People’s Republic of China and , Beijing 100049, People’s Republic of China

Funding

National Natural Science Foundation of China · The Strategic Priority Research Program of the Chinese Academy of Science

References (22)

Show source-provided references
1. 2019
2. A novel variable mode emitter for electrospray thrusters
3. ST7-DRS colloid thruster system development and performance summary
4. Ground and on-orbit thruster performance comparison for the Lisa Pathfinder colloid micro-Newton thrusters
5. Colloid micro-Newton thruster development for the ST7-DRS and LISA missions
6. Component-level development and testing of a colloid micro-thruster (CMT) system for the LISA mission
7. LISA colloid micro-thruster technology development plan and progress
8. Analysis of the electrospray plume from the EMI-Im propellant externally wetted on a tungsten needle
9. Ionic liquid ion sources: Characterization of externally wetted emitters10.1016/j.jcis.2004.08.132 ↗
10. A fully microfabricated externally wetted electrospray thruster
11. Ionic liquid dual-mode spacecraft propulsion assessment10.2514/1.49959 ↗
12. Mission capability gains from multi-mode propulsion thrust profile variations for a plane change maneuver
13. Combined high and low thrust propulsion for fast piloted Mars missions
14. Spacecraft optimization with combined chemical-electric propulsion10.2514/3.26623 ↗
15. Bimodal propulsion system using ionic liquid propellant for pico- and nano-satellite applications
16. Characterization of a novel ionic liquid monopropellant for multi-mode propulsion
17. Study on the emitter infiltration of needle-capillary ionic liquid electrospray thruster10.1063/5.0040081 ↗
18. Salt effects on Diels–Alder reaction kinetics10.1021/cr990410+ ↗
19. The room temperature ionic liquid 1-ethyl-3-methylimidazolium tetrafluoroborate: Electrochemical couples and physical properties10.1149/1.1838106 ↗
20. Ionic liquid ion sources: Suppression of electrochemical reactions using voltage alternation10.1016/j.jcis.2004.07.037 ↗
21. Fabrication of externally wetted emitter for ionic liquid electrospray thruster by low-speed wire cutting combined with electrochemical etching10.1063/5.0072630 ↗
22. Electrowetting of ionic liquids: Contact angle saturation and irreversibility10.1021/jp902393r ↗