New England Space Works proposes to magnetically control the thrust plume from an RF plasma thruster. Two issues will be addressed, plume divergence and thrust direction. Plume divergence is controlled by the point in the exhaust where the plasma breaks free of the magnetic field lines. The physical model for the thrust divergence will be verified, then used to design a unique magnetic circuit to minimize divergence. The use of magnetic coils to change thrust direction without use of gimbals will also be examined. This work will enhance the RF plasma thruster, uniquely suited for low power operation because it does not have the hollow cathode propellant losses of gridded ion and Hall thrusters, nor the propellant loss at end of pulse of the PPT. Anticipated Benefits and
Potential Commercial Applications: Manufacturers of spacecraft and thrusters for spacecraft are potential customers. The high specific impulse of electric propulsion compared to chemical is attractive to customers because of the dramatic reduction in propellant mass.
