| Constellations composed up of micro-satellites for different purpose will play an important role in satellite application. Precision positions control for each satellite in the constellation is required, which appeals for advanced orbit propulsion technologies. Because of micro-satellite's rigid limitations over volume and weight, propulsion systems in micro-satellite should have such properties as low volume and weight, low energy consumption, low cost, easy-control and low contamination. With advantages of simple and reliable in structure, high Isp and easy control over a wide range of thrust, Pulsed Plasma Thruster (PPT) is very suitable for micro-satellite's orbit control and high precision attitude control.Based on the early study of PPT in CSSAR, new research work has been carried out on the thruster structure, energy store capacitor, power supply unit, circuit of ignition, measurement of electric properties, thrust and Isp of PPT. A PPT test set has been made, and a measurement system of PPT's electric properties (voltage and discharge current), Isp and thrust has been established. Measurement of electric properties of the PPT and its Isp, thrust has been carried out. Test results have shown that with discharge energy of 40 J, our PPT's thrust has reached more than 0.605 mN, and its Isp is 1188 s and weight is 4.2Kg, which reaches the level of current PPT used in the world.
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