[0] https://en.wikipedia.org/wiki/Field-emission_electric_propul... [1] https://www.esa.int/Enabling_Support/Space_Engineering_Techn...
The FEEP thrusters I've seen had a hefty power penalty to keep it on standby, and a long warmup time. Cold gas uses more propellant mass per unit impulse, but it can still come out ahead in total size/weight/power.
I don't know the power budget for the satellite, but we can make an educated guess : the occulter is 1.4 meter diameter, or a surface area of 1.54 square meter. That's an upper bound for the surface area of the solar panels - there's nothing sticking out beyond the disk, that would interfere with observations.
Solar power at earth is about 1.3kW/sqm, solar panels are maybe 20% to 30% efficient. That puts you in the ballpark of 400 to 600W.
150W on standby would be a pretty big bite out of your power budget.