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Ying Zhang, Dawei Guo and Yuntian Yang
This work describes the advances on a micro-newton torsional thrust balance for ionic liquid electrospray thruster (ILET) being developed in the National University of Defense Technology. The torsional thrust balance adopts an asymmetric pendulum arm abo...
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Yuntian Yang, Dawei Guo, Xiaokang Li, Leimin Deng, Bixuan Che and Mousen Cheng
The porous-media-based electrospray thruster is a cutting-edge micropropulsion technology that can revolutionize the capabilities of microsatellites. This paper reports the design, fabrication, and characterization of a novel porous-media borosilicate gl...
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Ethan Dale, Benjamin Jorns and Alec Gallimore
The research challenges for electric propulsion technologies are examined in the context of s-curve development cycles. It is shown that the need for research is driven both by the application as well as relative maturity of the technology. For flight qu...
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Nolan M. Uchizono, Adam L. Collins, Anirudh Thuppul, Peter L. Wright, Daniel Q. Eckhardt, John Ziemer and Richard E. Wirz
Electrospray thruster life and mission performance are strongly influenced by grid impingement, the extent of which can be correlated with emission modes that occur at steady-state extraction voltages, and thruster command transients. Most notably, we ex...
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Anirudh Thuppul, Peter L. Wright, Adam L. Collins, John K. Ziemer and Richard E. Wirz
Ionic liquid electrospray thrusters are capable of producing microNewton precision thrust at a high thrust?power ratio but have yet to demonstrate lifetimes that are suitable for most missions. Accumulation of propellant on the extractor and accelerator ...
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Benjamin St. Peter, Rainer A. Dressler, Yu-hui Chiu and Timothy Fedkiw
We report on the development of a software tool, the Electrospray Propulsion Engineering Toolkit (ESPET), that is currently being shared as a web application with the purpose to accelerate the development of electrospray thruster arrays for space propuls...
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Jared M. Magnusson, Adam L. Collins and Richard E. Wirz
To better characterize the lifetime and performance of electrospray thrusters, electron emission due to electrode impingement by the propellant cation 1-ethyl-3-methylimidazolium (EMI+) has been evaluated with semi-empirical modeling techniques. Results ...
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