Liquid-Fed Pulsed Plasma Thruster for Propelling Nanosatellites
A novel micro liquid fed pulsed plasma thruster offers increased efficiency and lifetime for nanosatellites and CubeSats by eliminating the need for a propellant feed mechanism.
Researchers at Purdue University have developed a liquid fed pulsed plasma thruster (LF-PPT) for use in nanosatellites. Contemporary solid/gas phase propellants have been employed with limited success in nanosatellites, stemming from low efficiencies, limited operational lifetime, contamination issues, and complex/bulky injection systems. To remediate these disadvantageous qualities and make thruster systems more applicable to nanosatelitte designs, this technology presents a novel micro LF-PPT propulsion system comprised of a pulsed plasma accelerator and a low-energy surface flashover igniter. No propellant feed mechanism is needed with this design, making it beneficial for nanosatellite application due to their volumetric constraints. Pentaphenyl trimethyl trisiloxan was used as a propellant for testing parameters of the system including igniter breakdown, plasma dynamics, and exhaust velocity.
Advantages:
-Increased efficiency
-Smaller sized propulsion system
-Increased lifetime
-"Green" propulsion system
Potential Applications:
-Nanosatellites
-CubeSats
TRL: 3
Intellectual Property:
Provisional-Patent, 2019-06-25, United States | Utility Patent, 2020-06-23, United States | CON-Patent, N/A, United States
Keywords: liquid fed pulsed plasma thruster, LF-PPT, nanosatellites, propulsion system, pulsed plasma accelerator, surface flashover igniter, CubeSats, "Green" propulsion system, micro LF-PPT, spacecraft propulsion