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 by NASA and the broader electric propulsion community. Large investments in running the long duration test programs (> 20 kHrs) at NASA GRC can be reduced with computer models and allow more focus on exploring the NEXT ion thruster design for future space missions. The current state of electric propulsion modeling relies heavily on empirical data frequently taken directly from the device of interest and relies on numerous computational "knobs". A self-consistent particle model that minimizes the number of free parameters used in thruster modeling, and allows accurate electric thruster simulations is desired. We propose a kinetic model that simulates the dynamic electric fields inside the NEXT ion thruster discharge chamber plasma. This will be the first time that this has been done. In addition kinetic erosion models will be used for modeling the ionimpingement effects on thruster components. We envision one seamless model of the plasma from emission within the hollow cathode to ejection to outer space in the exhaust plume. This model will help NASA GRC to predict the lifetime operation of the high power ion propulsion options for earth-orbital applications.

Electric propulsion is important to other government agencies including the Air Force and the Navy. Air Force electric propulsion codes will benefit from additional/advanced plasmasurface interaction models available in our tools. The multi-billion dollar military and commercial satellite industries design and develop electric thrusters similar to the one used at NASA for the purposes of satellite station keeping and orbit changing maneuvers in space. These industries would benefit from the user-friendly computational tools, which include more realistic physics models, to study the ion thruster plasma. The innovations proposed in this work will also benefit the ion source and plasma processing industries.

The off-the-shelf ion thruster discharge chamber computational tools should reduce the time spent by NASA employees developing these tools for electric propulsion systems such as the 40-cm diameter NEXT thruster. The easy-to-use and user-friendly graphical user interface plasma softwares from Tech-X are viable high performance modeling tools for NASA to study the current and future electric thruster concepts which will help their planning for future space missions. Also these tools can be applied to modeling Hall thrusters such as the HiVHAC thruster, which is currently being developed at NASA GRC. The fully electromagnetic capabilities in these codes make them an ideal tool for modeling cathodeless RF ionization schemes as well.

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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