The invention discloses a xenon pump cold plate for electric propulsion spacecraft system-level ignition tests. The xenon pump cold plate for electric propulsion spacecraft system-level ignition testsis provided with integratedly connected plate-fin part and inverted cone part, wherein cutting plane processing is performed on the top of the arc surface of the external inverted cone part; the center of the cutting plane is provided with a connecting hole for connecting a cold head; and the plate-fin thickness of the cold plate employs gradual changing processing, thus the closer to the cold head, the thicker the thickness of the plate-fin is, and the farther away from the cold head, the thinner the thickness of the plate fin is. The invention also discloses a xenon pump with the cold plate. The xenon pump cold plate for electric propulsion spacecraft system-level ignition tests is suitable for spacecraft ignition tests taking an electric thruster as power, can extract the working medium xenon, and can guarantee the pressure demand of containers.