In order to provide a reference for the optimization design of arcjet thruster for small satellite propulsion system, very-low-power arcjet thrusters with input power of a few watts to tens of watts and performance testing system, including an indirect measurement system of aerodynamic small thrust were designed and built up. The generated thrust was measured with the variations of operating parameters of arc voltage, arc current and gas flow rates. Experimental results show that under the conditions of gas flow rate of 4.5~10.5 mg/s and and input power of 3~35 W, the largest thrust generated by the very-low-power arcjet is about 9.7 mN, and the maximum specific impulse is about 110 s. The narrow throat and large expansion ratio can be beneficial for the performance of very-low-power arcjet. When the arc current is increased from 10~110 mA, the arc voltage is increased from 210~280 V. In addition, the gas discharge mode may be different from traditional arcjet.
; 潘文霞
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