TY  - JOUR
AB  - Purpose– Field emission electric propulsion (FEEP) thruster is a type of electric propulsion based on space‐proven indium liquid metal ion sources. The lifetime of FEEP thruster limits its application in space. A better method to improve its lifetime is the reduction of emission current. This paper aims to discuss the minimum emission current of operating FEEP thrusters.Design/methodology/approach– In this work, theoretical models, including fluid‐flow model and ion formation model, are analyzed. Current densities of these models are discussed and the minimum emission current is calculated.Findings– There are few equilibrium states under low emission current conditions. However, the minimum emission current is the only stable state at which the FEEP thruster can operate.Research limitations/implications– This analysis is mainly based on the needle indium FEEP, which is compared indirectly with experiments of gallium.Practical implications– This paper attempts to help designers choose appropriate electric parameters to improve the lifetime of FEEP.Originality/value– By introducing and analyzing theoretical models, this paper calculates the minimum emission current for stable operation of FEEP.
VL  - 82
IS  - 5
SN  - 0002-2667
DO  - 10.1108/00022661011092929
UR  - https://doi.org/10.1108/00022661011092929
AU  - Junyi Duan
AU  - Xiaoming Kang
AU  - Wansheng Zhao
PY  - 2010
Y1  - 2010/01/01
TI  - Minimum emission current of indium‐field emission electric propulsion thruster
T2  - Aircraft Engineering and Aerospace Technology
PB  - Emerald Group Publishing Limited
SP  - 284
EP  - 287
Y2  - 2024/05/08
ER  -