Fabrication and Testing of Micron-Sized Cold-Gas Thrusters
Fabrication and Testing of Micron-Sized Cold-Gas Thrusters
复制标题
微米级冷气推进器的制造和测试
DOI：
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发表时间：
2000
期刊：
影响因子：
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通讯作者：
K. Breuer
中科院分区：
文献类型：
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作者：
R. Bayt;K. Breuer
轮廓收敛发散微喷嘴已被制造和测试的加速气流超音速。挤出的二维器件，与平均19微米和35微米的最小喉宽，制造深反应离子刻蚀。通过喷嘴的质量流效率范围从87%到98%，并在实验误差范围内的2-D Navier-Stokes流体模拟雷诺数350-3800的预测。膨胀比为16.9：1的喷管的推力在97 psia的燃烧室压力下测得为11.3 mN。这对应于650 m/s的出口速度，对于300 K的室温度，该出口速度为4.1马赫，并且Isp效率为93%。推力和Isp效率被发现偏离2-D数值模型在低雷诺数，并提供了可能的原因，但尚未确定的确切机制。术语a声速Cd放电系数D喉宽出现：推进与动力杂志，2000年
Contoured converging-diverging micronozzles have been fabricated and tested for the acceleration of gas flows to supersonic velocities. Extruded two-dimensional devices, with minimum throat widths averaging 19 microns and 35 microns, are fabricated by deep reactive ion etching. Mass flow efficiencies through the nozzles range from 87% to 98% and are within experimental error to those predicted by a 2-D Navier-Stokes fluid simulation for Reynolds numbers 350-3800. The thrust of a 16.9 to 1 expansion ratio nozzle was measured to be 11.3 mN at 97 psia chamber pressure. This corresponds to an exit velocity of 650 m/s, which is Mach 4.1 for a chamber temperature of 300 K, and an Isp efficiency of 93%. Thrust and Isp efficiency are found to deviate considerably from the 2-D numerical model at low Reynolds, and possible causes are offered, but the definitive mechanism has not been identified. NOMENCLATURE a Speed of Sound Cd Coefficient of Discharge D Throat Width To Appear: Journal of Propulsion and Power, 2000