Vacuum solid-state ion-conducting silver source for application in field emission electric propulsion systems

Structure, conductivity, and ion emission properties of RbAg4I5 solid electrolyte film prepared by pulsed laser deposition*

“…[16,17] FEEP systems with SSEs can be used on space-constrained micro-spacecraft to enable on-orbit controls such as raising, lowering of its altitude and repositioning of the spacecraft owing to the ability of the source to produce controllable thrust within µN range. [18] For example, emission of oxygen ions from an oxygen ion-beam source with solid-state ion conductor was reported by Wilbur et al [19] in 2005. In addition, continuous silver ions emissions from an Ag + ion source based on (AgI) 0.5 -(AgPO 3 ) 0.5 SSE was reported by Escher et al in 2006.…”

“…[20] RbAg 4 I 5 was prepared and investigated in the mid-1960s. [18] In 1967, Owens et al revealed that crystalline compound RbAg 4 I 5 exhibited superior ion conductivity of more than 10 1 S/m at 25 • C with negligible electronic contribution of < 10 −9 S/cm. [21] Since then, RbAg 4 I 5 SSEs have been extensively studied.…”

“…[21] Since then, RbAg 4 I 5 SSEs have been extensively studied. In 2016, Tolstogouzov et al [18] reported an Ag + ion-beam source based on RbAg 4 I 5 solid state electrolyte films, generating stable silver ion currents.…”

“…Figure 7(a) shows the volt-ampere characteristic (I-U acc )of the silver ion source at the working temperature of 196 • C, which shows an increasing tendency in total. When increasing and decreasing the acceleration potential, two I-U acc curves with a hysteresis effect are observed, which results from the inertial character of Ag + migration through the RbAg 4 I 5 solid state electrolyte film [18]. …”

Extraction process of charged droplets in ultrasonic electric propulsion system: An experimental study

“…Different EP thrusters, such as ion engine, colloid thruster, and field emission electric propulsion thruster have been used in orbit transfer of a satellite, attitude control, stationkeeping, etc. [6][7][8][9] However, EP thrusters, such as colloid thrusters, have difficulty in the integration of numerous emitters, which result in lower flow rate of propellant, and make it difficult to achieve a larger thrust density. 10 As an attempt to increase the thrust density of a colloid thruster, many emitters have been integrated on an electrospray nozzle according to certain arrays.…”