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| 预失真半导体激光列阵技术 | |
| 引用本文： | 蔡然,荣健,曾岚,薛蔡,陈建国,蔡贵顺,胡诗杰,曹捷,董吉辉,李晓峰,胡渝,林为干.预失真半导体激光列阵技术[J].发光学报,2008,29(2):342-352. |
| 作者姓名： | 蔡然 荣健 曾岚 薛蔡 陈建国 蔡贵顺 胡诗杰 曹捷 董吉辉 李晓峰 胡渝 林为干 |
| 作者单位： | 1. 电子科技大学,应用所,四川,成都,610054 2. 中国工程物理研究院,电子工程研究所,四川,绵阳,621900 3. 四川大学,电子信息学院,四川,成都,610064 4. 中国科学院,光电研究所,四川,成都,610209 5. 中国科学院,西安光学精密机械研究所,陕西,西安,710119 6. 中国科学院,上海光学精密机械研究所,上海,201800 |
| 摘 要： | 相干半导体激光列阵体积小、重量轻,输出能量密度高,非常适于用作对光源尺寸要求苛刻的航天激光光源。为避免随航天器在轨运行的半导体列阵经受变化梯度剧烈的恒星、行星、空间低温热沉的交替加热和冷却的影响,以便能够正常工作,采用潜望式结构设计,将列阵置于舱内,列阵向航天器外输出激光必须经由舱外输出反射镜完成。然而,舱外输出反射镜受周围热环境影响和列阵输出激光束照射,会产生随机热变形,导致输出舱外的激光能量发散;并且,舱外输出反射镜面热变形导致镜面法向偏转,使得输出光束产生较大的指向偏转误差,这极大地降低了能够作用于目标之上的激光束的能量密度,严重恶化输出舱外的光束质量。通过理论推导结合ANSYS有限元分析软件和相关实验,在研究清楚相干半导体激光列阵作为航天激光源的构造、其光场与周围热环境共同作用于舱外输出反射镜的规律与特点后,给出了航天预失真半导体激光列阵激光源技术,通过回波法适时测量舱外输出反射镜引起的波前畸变,处理器配合D/A和高压放大器,驱动驱动器,使舱内添加的反射镜预失真成形,适时使列阵输出产生预失真波前畸变,以抵消舱外输出反射镜的热变形对输出舱外的激光束的影响。相关系统运行实验结果显示,此技术使半导体激光列阵能够适应宇航环境,向舱外输出保障质量的激光束。 |
| 关 键 词： | 相干半导体激光列阵 航天激光源 宇航环境 预失真 光束质量 |
| 文章编号： | 1000-7032(2008)02-0342-11 |
| 修稿时间： | 2007年8月25日 |
The Study of the Space-borne Phase-locked Laser Diode Array Technology with Predistortion |
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| CAI Ran,RONG Jian,ZENG Lan,XUE Cai,CHEN Jian-guo,CAI Gui-shun,HU Shi-jie,CAO Jie,DONG Ji-hui,LI Xiao-feng,HU Yu,LIN Wei-gan.The Study of the Space-borne Phase-locked Laser Diode Array Technology with Predistortion[J].Chinese Journal of Luminescence,2008,29(2):342-352. | |
| Authors: | CAI Ran RONG Jian ZENG Lan XUE Cai CHEN Jian-guo CAI Gui-shun HU Shi-jie CAO Jie DONG Ji-hui LI Xiao-feng HU Yu LIN Wei-gan |
| Abstract: | In active remote sensing, electrooptical countermeasures, wireless optical remote transmitting and so on, the space-borne laser source carried by a space vehicle is indispensable, the function is unique, powerful and irreplaceable. For accomplishing the intended result in astronautical engineering or in aeronautical engineering, it is necessary to make the intended aim, whose size is finite, be irradiated by laser beam emitting from a right space-borne laser source, and the energy density of the laser beam that irradiates the aim must be enough high. Phase-locked laser diode array is small in size and light in weight, it is quite fit for performing the function of high power space-borne laser whose size must be exigent proper. Meanwhile, in space, the space thermal environment will be influenced by star, planet and space heat sink, a space vehicle is heated and cooled by turns, the change in temperature is violent, to avoid being damaged in space, in this paper, a phase-locked laser diode array who acts as the space-borne laser source in a space vehicle is placed inside the space capsule, only is reflected by the extravehicular reflecting mirrors, the laser beam that emits from the phase-locked laser diode array can pass through the outgoing mirror of the space-borne laser source, and then can transmit into space, the structure of the whole space-borne laser source is periscopic, even so, induced by the varied surrounding space thermal environment, and aggravated by the laser beam that the extravehicular reflecting mirror's reflect, the extravehicular reflecting mirrors will deform stochastically, so the output energy of the space-borne laser source is diverged, at the same time, the normal line of each reflecting mirror surface turns due to the reflecting mirror thermal distortion, so corresponding transferred laser beam has a large deflect, therefore the energy density of the laser beam that can be transmitted to the intended aim and then can treat the aim to be detracted greatly, the performance of the space-borne phase-locked laser diode array will suffer seriously. By way of theoretical derivation, finite element analysis and pertinent experiment, this paper presents clear ideas on the configuration of the space-borne laser source whose emitter is just a phase-locked laser diode array, on characteristics of the space thermal environment that can impact the extravehicular reflecting mirrors, on the optoelectrical field distribution of the phase-locked laser diode array who irradiates the extravehicular reflecting mirrors. Then it makes the laws that govern the action of the deformation of the extravehicular reflecting mirror clear. After that, the novel predistortion technology is presented. To perform the proposed technology in the proposed periscopic space-borne laser source, firstly, the wavefront error induced by the deformation of the extravehicular reflecting mirrors is sensed by the special sensing probe by means of the special echo wave method, after processed by the special processor, the controlled quantity for compensating the outgrowth of the deformation of the extravehicular reflecting mirrors can be obtained, with suitable D/A, high voltage amplifier, the actuating mechanism makes the additive reflecting mirror inside the capsule shape correctly in time, so with right predistortion, after it to be done by the additive reflecting mirror, the laser beam that will be reflected by the extravehicular reflecting mirrors won't be deteriorated by the deformation of the extravehicular reflecting mirror, the experiment demonstrates that the proposed technology makes a space-borne laser diode array adapts to the space thermal environment, guarantees the quality of its output laser beam, this is significant for that laser diode array should be employed in space. |
| Keywords: | phase-locked laser diode array space-borne laser source space flight environment predistortion beam quality |
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