靶材厚度对透射式激光烧蚀性能的影响

推进技术 ›› 2017, Vol. 38 ›› Issue (7): 1669-1674.

靶材厚度对透射式激光烧蚀性能的影响

刘昭然¹,洪延姬¹,叶继飞¹,陈庚²

装备学院激光推进及其应用国家重点实验室，北京 101416,装备学院激光推进及其应用国家重点实验室，北京 101416,装备学院激光推进及其应用国家重点实验室，北京 101416,中国人民解放军63771部队，陕西渭南 714000

发布日期:2021-08-15
作者简介:刘昭然，男，博士生，研究领域为激光航天应用技术。
基金资助:
国家自然科学基金(11602304)。

Effects of Propellant Thickness on Laser Ablation Performance in Transmission Mode

State Key Laboratory of Laser Propulsion & Application，Equipment Academy，Beijing 101416，China,State Key Laboratory of Laser Propulsion & Application，Equipment Academy，Beijing 101416，China,State Key Laboratory of Laser Propulsion & Application，Equipment Academy，Beijing 101416，China and PLA 63771 Unit，Weinan 714000，China

Published:2021-08-15

摘要/Abstract

摘要： 为从微观角度更加直观地研究靶材厚度对透射式激光烧蚀微推进性能的影响，采用刮涂法制作了6种不同厚度的聚叠氮缩水甘油醚/硝化棉(GAP/NC)共混聚合物掺杂红外吸收染料(IR)的烧蚀靶材，基于高速相机和高倍显微镜搭建了羽流观测系统和靶坑观测系统，研究了在纳秒脉冲激光辐照下，烧蚀厚度分别为33μm，53μm，78μm，104μm，125μm 和144μm的GAP/NC+IR靶材所产生的羽流流场随时间演变的微观过程和靶坑形貌的微观特征，从而建立了透射式激光烧蚀的微观特征与宏观推进性能的联系，进一步分析了其所表征的推进性能的优劣。结果表明:随着靶材厚度的增加，靶材的前沿喷射物初始速度由2100m/s单调降至1340m/s左右，预示着烧蚀比冲的减小；喷射物中大颗粒凝聚态物质增多，靶坑的体积增大，喷射质量增加，预示着烧蚀产生的冲量和冲量耦合系数的增大；喷射发散角减小，羽流方向性变好，但烧蚀过程对基底的冲击程度增强。

关键词: 激光烧蚀；透射式；靶材厚度；羽流；靶坑；激光推进

Abstract: In order to study the effects of the propellant thickness on the performance of laser ablation from microscopic，6 kinds of ablation target，taking GAP/NC polymer blend doped with infrared absorbing dye(IR) as propellant，were made with different thickness by knife coating. The ablation ejections and shockwave generated by nanosecond pulse laser were recorded by high-speed camera and the ablation crater was observed by high-power microscope. With the help of the observing system constructed in this paper，the relationship between microscopic characteristics，including plume evolution process and ablation crater，and macro propulsion performance was established. The ablation performance of GAP/NC+IR propellant with the thickness of 33μm，53μm，78μm，104μm，125μm and 144μm were studied respectively. The experimental results show that when propellant thickness increases，the fraction of large condensed matter in ejections and the volume of ablation crater both grow，indicating larger mass of ejections and larger momentum and momentum coupling efficiency，while the ejection velocity of front particles slows down from 2100m/s to 1340m/s，resulting in the decrease of specific impulse. Moreover，thinner propellant can weaken the impact of ablation process on the substrate，while leading a larger divergence angle of ejections at the same time.

Key words: Laser ablation；Transmission mode；Propellant thickness；Plume；Ablation crater；Laser propulsion

刘昭然,洪延姬,叶继飞,陈庚. 靶材厚度对透射式激光烧蚀性能的影响[J]. 推进技术, 2017, 38(7): 1669-1674.

LIU Zhao-ran¹,HONG Yan-ji¹,YE Ji-fei¹,CHEN Geng². Effects of Propellant Thickness on Laser Ablation Performance in Transmission Mode[J]. Journal of Propulsion Technology, 2017, 38(7): 1669-1674.

参考文献

[1] Luke J R, Phipps C R, Mcduff G G. Laser Plasma Thruster[J]. Applied Physics A, 2003, 77(2): 343-348.
[2] 唐志平. 烧蚀模式激光推进的机理和应用探索[J]. 中国科学技术大学学报, 2007, 37(10): 1300-1305.
[3] Phipps C R, Luke J R, McDuff G G, et al. A Laser-Ablation-Based Micro-Rocket[C]. Maui, Hawaii: The 33rd Plasma Dynamics and Lasers Conference, 2002.
[4] Phipps C R, Luke J R, McDuff G G, et al. Laser-Ablation-Powered Mini-Thruster[J]. Proceedings of SPIE - The International Society for Optical Engineering, 2002, 4760: 833-842.
[5] 叶继飞, 洪延姬, 王广宇, 等. 透射式激光等离子体微烧蚀推力性能研究[J]. 推进技术, 2010, 31(2): 247-251. (YE Ji-fei, HONG Yan-ji, WANG Guang-yu, et al. Thrust Performance Study on Laser Plasma Micro Ablation with Transmission Mode[J]. Journal of Propulsion Technology, 2010, 31(2): 247-251.)
[6] 叶继飞, 洪延姬, 王广宇, 等. 激光等离子体微推进技术的研究进展[J]. 中国光学, 2011, 4(4): 319-326.
[7] 洪延姬, 李修乾, 王殿恺, 等. 对凝聚态工质激光推进的思考[J]. 推进技术, 2009, 30(5): 618-624. (HONG Yan-ji, LI Xiu-qian, WANG Dian-kai, et al. Some Thoughts on Condensed Propellants for Laser Propulsion[J]. Journal of Propulsion Technology, 2009, 30(5): 618-624.)
[8] 南宝江, 张钢锤, 吴平, 等. 含能工质激光烧蚀推进效率分析[J]. 推进技术, 2007, 28(5): 478-480. (NAN Bao-jiang, ZHANG Gang-chui, WU Ping, et al.Analysis of Energy Conversion Efficiency of Solid Propellant for Laser Ablative Propulsion[J]. Journal of Propulsion Technology, 2007, 28(5): 478-480.)
[9] 蔡建. 激光微推进的原理和应用研究[D]. 合肥:中国科学技术大学, 2007.
[10] Phipps C R, Luke J R, Helgeson W, et al. Performance Test Results for the Laser-Powered Microthruster[C]. Nara, Japan: Beamed Energy Propulsion: 4th International Symposium, 2005.
[11] Phipps C, Luke J R, Lippert T, et al. Micropropulsion Using a Laser Ablation Jet[J]. Journal of Propulsion and Power, 2004, 20(6): 1000-1011.
[12] Phipps C, Luke J, Lippert T. Laser Ablation of Organic Coatings as a Basis for Micropropulsion[J]. Thin Solid Films, 2004, 453: 573-583.
[13] Phipps C R, Ii D B S, Royse R W, et al. Very High Coupling Coefficients at Low Laser Fluence with a Structured Target[C]. USA: Proceedings of SPIE - The International Society for Optical Engineering, 2000: 931-938.
[14] Jian C, Long L, Yu D, et al. Experimental and Numerical Investigation of Propellant of Different Thickness for Laser Micro Propulsion[C]. Scottsdale, Arizona: Beamed Energy Propulsion: 6th International Symposium, 2010.
[15] 童慧峰, 唐志平. 靶结构对烧蚀模式激光推进效应影响的数值模拟[J]. 高压物理学报, 2011, 25(3): 227-234.
[16] 李龙, 胡晓军, 唐志平. 激光化学微推进推力性能的实验研究[J]. 兵工学报, 2014, 35(6): 908-914.
[17] L Urech. Design and Characterization of Energetic Polymers Applied in Laser Space Propulsion[D]. Zürich: Eidgen?ssische Technische Hochschule Zürich, 2007.
[18] Hauer M. Laser Ablation of Polymers Studied by Time Resolved Methods[D]. Zürich: Swiss Federal Institute of Technology Zürich, 2004.　　　　　　　　　　　　　　收稿日期:2016-10-14；修订日期:2016-12-28。基金项目:国家自然科学基金(11602304)。作者简介:刘昭然,男,博士生,研究领域为激光航天应用技术。E-mail: liuzhaoran168@126.com(编辑:张荣莉)