Abstract: Low orbit has the characteristic of short orbital period and small signal transmission delay.It has signifi-cant advantages for remote imaging,earth environmental detection,and communication constellation.The orbit perturba-tion of satellite caused by atmosphere drag must be compensated by propulsion system.Ion electric propulsion system has become the preferred solution due to the characteristic of long endurance,high specific impulse,and wide range thrust.Aimed to the earth’s filed model recovery and the low orbit satellite application requirements for ion electric propulsion,combing with the test result of LIPS-100 thruster,the key index decomposition of PPCU is conformed,and the corresponding key modules of PPCU is briefly described.Meanwhile performance test activities are applied to thruster and PPCU as the demonstration of prototype product technology.Data analysis result shows that the screen voltage output range of PPCU is 1 200.76 to 1 201.35 V.The stability and accuracy is better than 0.1% in 1 to 20.0 mN(the range of beam current is 18.0 to 367.0 mA)loading range.Anode current can be adjusted in the range of 0.100 0 to 3.000 0 A with a resolution of 1.0 mA,the magnet current resolution is better than 0.50 mA in the range of 0.0150 0 to 1.000 0 A.The thrust range reaches 1 to 20.0 mN and thrust resolution is better than 15 μN.Meanwhile,the correctness of establishing PPCU index and thrust throttling scheme are verified.The relative technology can be used in the engineering application.