多自由度激光干涉空间惯性质量块位姿测量  

Multi-degree-of-freedom measurement for space inertial test mass via laser interference

作　　者：马瑞[1,3] 李楠 何建国[2] 张建泉 黄旻[2,3] MA Rui;LI Nan;HE Jianguo;ZHANG Jianquan;HUANG Min(Key Laboratory of Space Utilization,Technology and Engineering Center for Space Utilization,Chinese Academy of Sciences,Beijing 100094,China;Optical Imaging Technology Lab,Aerospace Information Research Institute,Chinese Academy of Sciences,Beijing 100094,China;University of Chinese Academy of Sciences,Beijing 100094,China)

机构地区：[1]中国科学院空间应用工程与技术中心太空应用重点实验室,北京100094 [2]中国科学院空天信息创新研究院计算光学成像技术实验室,北京100094 [3]中国科学院大学,北京100094

出　　处：《光学精密工程》2023年第11期1593-1606,共14页Optics and Precision Engineering

基　　金：中国科学院科研仪器设备研制项目(No.YJKYYQ20210028)。

摘　　要：鉴于通过测量高精度的位移数据可以获得高精度的微重力加速度数据,进而服务于多种空间科学载荷的研究任务,提出了一种基于三组正交对称角锥棱镜的双频光路,利用外差干涉测量技术实现空间惯性质量块的六自由度位移和角度测量的方法。通过光路矢量分析建立了实际角锥棱镜的光路模型,考虑质量块在运动过程中带来的附加光程差,推导了各测量光路的光程变化与质量块六自由度位姿的函数关系。为了克服小角度近似法精度不高的缺陷,提出了利用数值计算法解耦姿态角进而获得相对位移的位姿解算算法。利用空间在轨位姿数据和随机位姿数据进行系统仿真。仿真结果表明:数值计算的位移误差小于0.02 fm,且该方法的计算误差不会随着飞行器振动的增大而变大,算法具有更高的精度和更好的适应性。最后,分析了系统的误差来源,在保证角度安装误差小于5 mrad、距离安装误差小于10μm且平行度小于2 mrad时,系统的姿态角测量误差小于0.017°,位移测量误差小于10 nm。本文提出的六自由度测量及解算方法也可以服务于其他精密加工与检测领域。High-precision displacement measurement can help realize high-precision microgravity,which can further sever a variety of space science payloads for research missions.In this study,we devised a dual-frequency interferometer based on three sets of orthogonal symmetric cube corner retroreflectors(CCRs)for measuring the six-degree-of-freedom(6DOF)pose of the spatial inertial test mass(TM)through heterodyne detection.We first established an optical model of the actual CCR,which considers the optical path difference caused by the motion of the TM,and derived the analytical relationship between the pose of the TM and the measured optical path change.Then,the attitude angles and displacements of the TM were calculated using the method of numerical analysis,which affords remarkably higher accuracy than does the traditional small-angle approximation method.Furthermore,the performance of our system was estimated using space in-orbit data and random data.The simulation results show that the displacement error was less than 0.02 fm even when the TM vibrated significantly,indicating that our method affords high accuracy and good adaptability.In addition,the error sources of the system were analyzed.The measurement errors for the attitude angle and displacement are less than 0.017°and 10 nm,respectively,when the angular installation error is below 5 mrad,the distance installation error is less than 10μm,and the parallelism is less than 2 mrad.The proposed 6DOF measurement and calculation method can also be used in various precision machining and detection applications.

关 键 词：精密测量 外差干涉测量 双频激光干涉 微重力 惯性传感 六自由度 

分 类 号：P164[天文地球—天文学]