Verifying the performance of an ASCENT-propelled pulsed-MPD propulsion system in the LEO enviornment in order to advance the dual-mode propulsion concept and utilization of ASCENT propellant.
Why space? Some phenomena affecting system performance cannot be feasibly recreated in ground testing. We must verify performance under the effects of microgravity, long-duration thermal cycling/exposure to hard vacuum, chemical environment, and other factors. Furthermore, testing the thruster in an actual use case provides the most reliable verification of system operation, while minimizing opportunities for false positive results.
This mission also has potential military relevance. Dual-mode propulsion balances two key mission requirements: responsiveness and mission lifetime. This method of propulsion could prove invaluale for responsive reconnaissance missions and formation flying. We are also furthering the understanding of the ASCENT propellant, and testing an electric propulsion thruster that is both novel, and commerically available.
Our first mission objective is to operate the PMPD propulsion system for one million pulses in LEO to execute a orbit-raising/loewring maneuver. Minimum success is defined by achieving 30% of ground-tested values in LEO.
The second mission objective is to determine the key performance metrics of our PMPD system while in LEO. These metrics include impulse bit, specific impulse, and efficiency of power to thrust conversion. Minimum success is defined by determining these value in LEO with less than 20% uncertainty.
The final primary mission objective is to record the propulson system health metrics during the thruster operation. These metrics include average power consumption, propellant injector temperature, propellant tank level, and current/voltage waveforms for the discharge and ignited circiuts.
