Propulsion systems including an electrically actuated valve

Abstract: Propulsion systems, such as electrospray thrusters, may include an electrically actuated valve to permit a selective flow of propellant to a thruster. The valve may be located and arranged such that it physically separates a propellant, such as a source of ions, from a thruster of the propulsion system. In some embodiments, the application of a voltage potential to the valve may wet a plurality of through holes formed in the valve with the propellant such that the propellant flows through the valve to the thruster. After the valve has been opened, the propulsion system may be operated normally.

https://patents.google.com/patent/US20200378371A1/

Description
Born out of my Master’s thesis work, this describes a solid-state microvalve designed for single-use flow application to an electrospray thruster.

The core challenge was to create a hyper-miniaturized component (smaller than your pinky fingernail) that could resist fluid intrusion during the harsh space-launch conditions that produce intense vibration and a rapid drop in pressure.

To do so, I used MEMS fabrication techniques to produce an array of microcapillaries with superhydrophobic geometry and coatings, that would allow electrowetting once voltage is applied on-orbit.