Inductively Coupled Electromagnetic (ICE) Thruster System Development for Small Spacecraft Propulsion Testing

In-space micropropulsion systems must strike a balance between simplicity, performance and mass/volume requirements, while having the flexibility of working with high-density propellants, and compatibility with the onboard power source. The Inductive Coupled Electromagnetic (ICE) thruster has the potential to achieve the highest level performance in all of these criteria, making it ideal for small satellite station-keeping and de-orbit maneuvers. The plasma generation is achieved with a small (∼4 cm diameter), spiral cut, porous stainless steel antenna with an integrated RF oscillator. The ICE thruster positions the coil driver, as well as all other circuit elements, immersed in the liquid propellant providing for a PPU energy transfer efficiency of near unity. The use of a porous material as the interface between the driver coil and plasma generation zone at the thruster exit eliminates the need for a complex, miniature high pressure gas feed and valve system.

This electromagnetic plasma thruster technology, operating at very small scale and power, will expand the capabilities of small spacecraft, which will benefit the commercial space industry and future NASA missions.

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