Abstract
Ionic liquid electrospray thrusters are notable for their small size, low mass, and high specific impulse, making them ideal for use in micro/nano satellites. This study evaluates the lifetime of an electrowetting ionic liquid electrospray thruster. Experimental results indicate that the decrease in emission current is attributed to electrochemical reactions that increase the curvature of the emitter tips and the increased flow resistance. The online replenishment of insufficient propellant is achieved using an electrowetting device, which restores the emission current. Over the entire test period, the thruster operated for a total of 331.81 h, consuming 2.68083 g of propellant. This study offers valuable insights for improving the lifetime and total impulse of ionic liquid electrospray thrusters.
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