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为了研究高超声速飞行器进气道内气体的放电特性,建立了低压高温环境下针-板放电实验系统,采用纳秒脉冲电源,开展了气压范围500~1 500 Pa、温度范围50~400℃条件下的直接驱动式放电实验。研究表明:当温度为50℃、气压为500 Pa时,针-板之间均存在形态为从针尖向板面扩散的柱状放电通道,而且随着气压的升高柱状通道逐渐向中心处收缩;在温度较低的情况下,峰值电压主要受气压的影响,并随着气压的升高而升高,在50℃、1 500 Pa时峰值电压达到了1 810 V;在温度较高时,若气压较低,温度的升高对峰值电压影响较小,而气压较高时,峰值电压的变化受温度影响较大,并随着温度的升高而降低,在1 500 Pa、400℃时峰值电压降为1 250 V。实验结果对后续研究超声速气流中纳秒脉冲放电特性与机理提供参考。
In order to study the discharge characteristics of the gas in the inlet of the hypersonic vehicle, a pin-plate discharge experiment system under low pressure and high temperature was established. The nanosecond pulse power was used to carry out the gas pressure range of 500 ~ 1 500 Pa and the temperature range of 50 ~ 400 ℃ Direct Drive Discharge Experiment. The results show that when the temperature is 50 ℃ and the pressure is 500 Pa, there are columnar discharge channels in the form of needle-to-plate diffusion between the needle and the plate, and the columnar channel shrinks gradually to the center as the pressure increases. In the case of lower temperature, the peak voltage is mainly influenced by air pressure and increases with the increase of air pressure. At 50 ℃, the peak voltage reaches 1 810 V at 1 500 Pa. If the temperature is high, The lower the pressure, the higher the temperature has little effect on the peak voltage, while the higher the pressure, the peak voltage changes are greatly affected by the temperature, and decreases with increasing temperature, the peak at 1 500 Pa, 400 ℃ The voltage drop is 1 250 V. The experimental results provide references for the follow-up study of nanosecond pulse discharge characteristics and mechanism in supersonic airflow.