Abstract: The solar array drive mechanism is partially exposed to the outside of the spacecraft, and the slip ring is easy to become the victim of the charge and discharge effect. The charging and discharging process of the slip ring under various radiation intensities is studied by using the ⁹⁰Sr-⁹⁰Y β source to simulate the high-energy electron environment in the middle and high Earth orbits. In the initial stage of the irradiation, the discharge of small amplitude is mostly the surface discharge. With the increase of the potential, the deep charging leads to the accumulation of a large number of electrons in the material. Beyond a certain threshold, the breakdown discharge occurs. Under the electron irradiation of 2.4 pA/cm² flux, the charging equilibrium potential of the slip ring reaches -3600 V, while under the 0.1 pA/cm² flux, the equilibrium potential is only -300 V. It is recommended to add a 3 mm protective aluminum plate to reduce the high-energy electron flux, to prevent the fault caused by charging and discharging of the slip ring in orbit. During the irradiation test, the working state of the slip ring is determined, with no abnormality being found. This indicates that the discharge during a short time irradiation has no effect on the performance of the slip ring.