Next-Generation Ion Thruster Design Tool to Support Future Space Missions

Computational tools that accurately predict the performance of electric propulsion devices are highly desirable and beneficial to NASA and the broader electric propulsion community. The current state-of-the-art in electric propulsion modeling relies heavily on empirical data and on numerous computational "knobs". In Phase I of this project, we developed the most detailed ion engine discharge chamber model that currently exists. This is a kinetic model that simulates all particles in the discharge chamber along with a physically correct simulation of the electric fields. In addition, kinetic erosion models are included for modeling the ion-impingement effects on thruster component erosion. For Phase II of this project, the goal is to make this sophisticated computer program a user friendly program that NASA and other governmental and industrial customers are able to utilize. In Phase II we will implement a number of advanced numerical routines to bring the computational time down to a commercially acceptable level. At the end of Phase II, NASA will have a highly sophisticated, user friendly ion engine discharge chamber modeling tool that will save time and expense in designing new and different size ion engines, as well as analyzing existing ion engine performance.

Electric propulsion is important to other government agencies including the Air Force and the Navy. Air Force electric propulsion will benefit from additional/advanced plasma-surface interaction models available in our computer code. The multi-billion dollar military and commercial satellite industries design and develop electric thrusters similar to the ones used at NASA for the purposes of satellite station keeping and orbit changing maneuvers in space. These industries could benefit from sophisticated, userfriendly computational tools, one of which we are developing. The innovations proposed in this work will also benefit the ion source and plasma processing industries which are utilized in materials processing applications and the electronics industries.

This ion thruster discharge chamber computational tool will reduce the time and expense that NASA incurs in the development of future ion engines. There are a number of space missions which ion engines could fulfill if different size engines could be designed quickly and cheaply. The computational tool being developed for this project will help to make this happen. This tool is also valuable in extending NASA's understanding of the current 40-cm diameter NEXT thruster that NASA GRC is currently testing for use in space. This tool can be used to extend the operating range of the NEXT ion engine to higher power levels, as is being considered in the NEXT STEP program. With some adjustments, this computational tool can simulate Hall thrusters, such as the HiVHAC thruster, which is currently being developed at NASA GRC.

This is early/mid-stage (TRL 6) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

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