Effect of nozzle geometry on the performance of laser ablative propulsion thruster
Effect of nozzle geometry on the performance of laser ablative propulsion thruster
复制标题
喷嘴几何形状对激光烧蚀推进器性能的影响
DOI：
10.1007/s00339-016-0040-9
复制
发表时间：
2016-05-01
影响因子：
2.7
通讯作者：
Peng, Jie
中科院分区：
文献类型：
--
作者：
Li, Long;Jiao, Long;Peng, Jie
喷管约束可以显著提高烧蚀模式激光推进发动机的性能。用CO_2激光器对“烧蚀模式”激光推进发动机喷管几何形状进行了实验研究。实验结果表明，在相同长度下，圆柱喷管推力器的推进性能优于扩张喷管推力器。采用不同的激光能量对圆柱喷管推力器进行了优化设计。结果表明，长径比α和推力器直径与光斑直径比β是影响推力器推进性能的两个重要因素。动量耦合系数C-m随α的增大而增大，而C-m随β的增大先增大后减小。
The performance of "ablation mode'' laser propulsion thrusters can be improved obviously by nozzle constraint. The nozzle geometry of "ablation mode'' laser propulsion thrusters has been studied experimentally with CO2 lasers. Experimental results indicate that the propulsion performance of cylindrical nozzle thrusters is better than expansionary nozzle thrusters at the same lengths. The cylindrical nozzle thrusters were optimized by different laser energies. The results show that two important factors, the length-to-diameter ratio alpha and the thruster diameter to laser-spot diameter ratio beta, affect the propulsion performance of the thruster obviously. The momentum coupling coefficient C-m increases with the increase of alpha, while C-m increases at first and then decreases with the increase of beta.