A robust stand for directly measuring pulsed thrust from micro-thrusters is presented. The method of electrostatic discs for in situ calibration was improved upon and simplified to allow convenient and accurate thrust measurement. The novel use of frictionless liquid gallium metal power interfaces for µN-level force measurement stands was also demonstrated. A series of detailed verification tests were performed to characterize the thrust stand’s overall operating range and accuracy. The stand can test single and multiple thrusters with a total mass of up to 10 kg and was found to be capable of resolving impulse bits between 0.27–600 µNs with 2–4% error in the optimal deflection range. Demonstration of the thrust stand’s capability and resilience to electromagnetic interference was accomplished by performing lifetime thrust tests on low-power Vacuum-Arc Thrusters operating with three different cathode fuels.

Vacuum arc thrusters (VATs) are a potentially useful technology for use as microthrusters, given their simplicity, low mass, and low-power requirements. However, further development is still needed to improve and mature their performance and operation. In an effort to improve thruster characteristics, we investigate the use of conically shaped convergent cathode surface profiles in a low-power coaxial VAT design. Experimental measurements of ion current density distribution, thrust, and erosion rate were taken for a range of cathode profiles and materials. Results show that modifying the profile of the cathode face can affect the plasma jet's plume distribution and even improve thrust production in certain cases. One likely cause of the thrust improvement is speculated to be increased charge exchange collisions resulting in a lower average ion charge state of the ejecting plasma.Index Terms-Cathode, diagnostics, ion charge state, ion current density distribution (ICDD), microthruster, plasma jet, propulsion, pulsed power, thrust stand, vacuum arc thruster (VAT).

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