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在喷管与聚光系统一体化设计时,聚光系统因其同时承担聚光和喷管两项功能而成为激光推力器的重要组成部分。通过改变聚光系统内表面的母线方程,可以改变点火区的大小、形状、点火区与聚光系统内表面的距离及喷管长度等参数,而这些参数都会对激光推力器的推进性能产生影响。针对不同的聚光系统构形建立了相应的点火模型,数值计算与实验结果一致,即当注入能量不超过60 J时,在喷管出口直径相同的条件下,抛物形喷管点聚焦方式比环聚焦方式所获得的冲量耦合系数大,可达38.84×10-5N.s/J;而冲量耦合系数对点火区与聚光系统内表面的距离及喷管长度等参数并不十分敏感。研究结果对于吸气式激光推力器的喷管构形设计具有指导意义。
In the integrated design of the nozzle and the condenser system, the condenser system is an important part of the laser thruster because of its two functions of focusing and nozzle. By changing the busbar equation of the inner surface of the condenser system, the parameters such as the size and shape of the ignition zone, the distance between the ignition zone and the inner surface of the condenser system and the length of the nozzle can be changed, and these parameters will affect the propulsion performance of the laser thruster . The corresponding ignition model was established for different condensing system configurations. The numerical calculation is consistent with the experimental results. That is, when the injection energy does not exceed 60 J, under the condition of the same nozzle outlet diameter, the parabolic nozzle point focusing mode ratio The coupling coefficient of momentum impulse obtained by the ring focusing method is as large as 38.84 × 10-5N.s / J. The impulse coupling coefficient is not sensitive to the distance between the ignition area and the inner surface of the condensing system and the nozzle length. The research results are instructive for nozzle configuration design of aspirating laser thruster.