基于旋转偏振光栅与快反镜的单探测器复合跟瞄系统  

Single detector composite tracking system based on rotating polarization grating and fast steering mirror

作　　者：王伟[1,2] 姜会林[1,2] 陈明策[3] 董岩 徐卿[3] 王立[3] 董科研[1,2] 安岩[1,2] WANG Wei;JIANG Huilin;CHEN Mingce;DONG Yan;XU Qing;WANG Li;DONG Keyan;AN Yan(School of Photoelectric Engineering,Changchun University of Science and Technology,Changchun 130022,China;Key Laboratory of Photoelectric Measurement and Control and Optical Information Transfer Technology of Ministry of Education,Changchun 130022,China;Space Optoelectronic Measurement and Perception Lab.,Beijing Institute of Control Engineering,Beijing 100190,China;School of Electric and Information Engineering,Changchun University of Science and Technology,Changchun 130022,China)

机构地区：[1]长春理工大学光电工程学院,长春130022 [2]光电测控与光信息传输技术教育部重点实验室,长春130022 [3]北京控制工程研究所空间光电测量与感知实验室,北京100190 [4]长春理工大学电子信息工程学院,长春130022

出　　处：《航空学报》2025年第3期60-72,共13页Acta Aeronautica et Astronautica Sinica

基　　金：光电测量与智能感知中关村开放实验室与北京控制工程研究所空间光电测量与感知实验室开放基金资助(LabSOMP-2022-10);吉林省重大科技专项(20230301002GX);国家自然科学基金青年科学基金项目(62305032);吉林省科技发展计划重点研发项目(20210201022GX)。

摘　　要：为满足激光通信系统的共形设计和实现轻小型化的空间激光通信组网,设计一种应用于机载平台下的基于偏振光栅与快反镜(FSM)的新型单探测器复合轴系统。针对旋转偏振光栅实际应用与理论之间的差异,将偏振光栅光束偏转问题与目标脱靶量之间进行关联,定义了目标位置与双偏振光栅角度关系,进行了偏振光栅光束偏转坐标构建及解耦。随后对复合系统偏振光栅单元与FSM单元进行设计,通过目标闭环试验检测了系统跟踪性能,结果表明,在5°@0.2 Hz载体扰动情况下,双偏振光栅方位轴、俯仰轴脱靶量闭环残差分别为126.1002μrad(RMS)与149.5309μrad(RMS),FSM方位轴、俯仰轴脱靶量闭环残差分别为3.4921μrad(RMS)与4.0131μrad(RMS),动态目标闭环控制双轴精跟踪残差为5.3197μrad(RMS),相比于Risley棱镜,光束偏转范围提升4倍,精度提升45.8%。整个跟踪过程中,两偏振光栅旋转角度值连续且平稳变化,满足轻量型机载平台对光电跟瞄设备的使用需求。To meet the conformal design of laser communication system and realize lightweight and miniaturiza⁃tion of space laser communication networking,a new single-detector composite axis system based on polariza⁃tion grating and Fast Steering Mirror(FSM)is designed for airborne platform.In response to the difference be⁃tween the practical application and theory of rotating polarization gratings,the relationship between the target position and the dual polarization gratings angles is defined by correlating the polarization grating beam deflec⁃tion problem with the target miss distance,and the polarization grating beam deflection coordinates are con⁃structed and decoupled.Then,the polarization grating unit and FSM unit of the composite system are de⁃signed,and the tracking performance of the system is tested through target closed-loop test.The results show that under the disturbance of 5°@0.2 Hz carrier,the closed-loop residual errors of the dual polarization gratings azimuth axis and pitch axis miss distance are respectively 126.1002μrad(RMS)and 149.5309μrad(RMS),the closed-loop residual errors of FSM azimuth axis and pitch axis miss distance are respectively 3.4921μrad(RMS)and 4.0131μrad(RMS),and the dual axis precision tracking residual error of dynamic target closedloop control with is 5.3197μrad(RMS).Compared to the Risley prism,the beam deflection range is increased by 4 times,and the accuracy is improved by 45.8%.During the whole tracking process,the rotation angle value of the two polarization grating changes continuously and steadily,which meets the needs of lightweight airborne platform for photoelectric tracking equipment.

关 键 词：光电跟瞄平台 光束偏转 双偏振光栅 跟踪性能 解耦 

分 类 号：V243.1[航空宇航科学与技术—飞行器设计]