Experimental Study On Performance And Stability Of Low Power Arcjet

Electric propulsion, which has an excellent performance, is taking the place of traditional chemical propulsion at present. Arcjet, one type of electric propulsion, is high at specific impulse and ratio of thrust, and good in capability of propellant. Thus it is being researched and applied in several countries. Our country has also developed Arcjet actively since 1990s. Low Power Arcjet, which works between the power level of 100W and 1000W, is an ideal micro propulsion device of attitude control and NSSK for small satellites and micro satellites. It is necessary to do study on it as a request of the development of small satellites and future aerospace tasks.A kind of low power arcjet structure is designed, produced and combined in this thesis. An experimental system was also built up. Macroscopic parameters, including arc voltage, thrust, pressure, are measured under different mass flux and current in vacuum environment, using Nitrogen as propellant. Performance parameters, such as specific impulse, efficiency, ratio of thrust and power and specific power, are acquired. The effect of mass flux, current, power, distance of electrodes and diameter of anode laryngeal on the performance and stability is analyzed. Laws are drawn, disadvantages are explained and solve is suggested.According to the conclusion of tests, changes are made toward the structure. Lot's of tests are carried out under different conditions. the results are compared with old ones. It is clear that arc voltage, thrust, specific impulse, efficiency and stability are all improved remarkably. The reason of these improvements are discussed as a base of lower down the power level without the debasement of performance and the alter of propellant by hydrogen or hydrazine.