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为了对适合小卫星使用的电弧加热推进系统的优化设计提供一定的参考,自行设计了输入电功率数瓦至数十瓦的小功率电弧等离子体推力器及其运行性能实验系统,包括一种气动小推力的间接测量系统。对四种不同喷管结构和尺寸的小功率电弧推力器,实验检测了所产生的推力随着弧电流和推进剂流量的变化。结果显示:在气流量4.5~10.5mg/s,输入功率3~35W的条件下,推力器产生的最大推力约为9.7mN,最大比冲约为110s;减小喉道直径,适当增加扩张比有助于提高小功率Arcjet的性能;当弧电流在10~110mA范围内变化时,弧电压的变化范围约为210~280V,气体的放电形式有别于传统的电弧加热推力器。
In order to provide reference for the optimization design of arc heating propulsion system suitable for small satellites, a small-power arc plasma thruster with input electric power of several watts to several tens of watts is designed by itself and its operating performance experimental system, including a small pneumatic Indirect measurement of thrust. For four kinds of low-power arc thrusters with different nozzle configurations and sizes, the thrust force generated by the experiment was measured as the arc current and the propellant flow rate changed. The results show that under the condition of gas flow of 4.5 ~ 10.5mg / s and input power of 3 ~ 35W, the maximum thrust generated by the thruster is about 9.7mN and the maximum specific impulse is about 110s. The throat diameter is reduced and the expansion ratio is appropriately increased Which helps to improve the performance of low-power Arcjet. When the arc current is in the range of 10 ~ 110mA, the variation range of arc voltage is about 210 ~ 280V, the discharge form of gas is different from the traditional arc-heated thruster.