电子测量与仪器学报

缪林良,米洒洒,王玮琳,金照南,杨志豪,欧阳君,杨晓非,陈实.航磁矢量测量的误差分析和补偿算法研究[J].电子测量与仪器学报,2021,35(12):15-23

航磁矢量测量的误差分析和补偿算法研究

Error analysis and compensation algorithm research ofaeromagnetic vector measurement

DOI：

英文关键词:aeromagnetic interference vector compensation carrier attitude helicopter aeromagnetic measurement system

基金项目:

作者	单位
缪林良	1.华中科技大学光学与电子信息学院
米洒洒	1.华中科技大学光学与电子信息学院
王玮琳	1.华中科技大学光学与电子信息学院
金照南	1.华中科技大学光学与电子信息学院
杨志豪	1.华中科技大学光学与电子信息学院
欧阳君	1.华中科技大学光学与电子信息学院
杨晓非	1.华中科技大学光学与电子信息学院
陈实	1.华中科技大学光学与电子信息学院

Author	Institution
Miao Linliang	1.School of Optics and Electronic Information, Huazhong University of Science and Technology
Mi Sasa	1.School of Optics and Electronic Information, Huazhong University of Science and Technology
Wang Weilin	1.School of Optics and Electronic Information, Huazhong University of Science and Technology
Jin Zhaonan	1.School of Optics and Electronic Information, Huazhong University of Science and Technology
Yang Zhihao	1.School of Optics and Electronic Information, Huazhong University of Science and Technology
Ouyang Jun	1.School of Optics and Electronic Information, Huazhong University of Science and Technology
Yang Xiaofei	1.School of Optics and Electronic Information, Huazhong University of Science and Technology
Chen Shi	1.School of Optics and Electronic Information, Huazhong University of Science and Technology

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中文摘要:

由机载平台引起的干扰场是航磁测量的主要误差来源之一,为提高地磁矢量的航空测量精度,设计了一种基于分量约束的矢量航磁补偿算法,建立了包含固定、感应和涡流磁干扰的补偿模型。通过引入惯性传感器获得的载体姿态信息,将补偿系数求解问题线性化,并采用最小二乘法进行了参数求解。仿真结果表明,算法可准确估计补偿系数,并将磁场矢量的均方根误差减小至 3 nT 以内。使用直升机航磁测量系统进行了飞行验证试验,补偿后总场的均方根误差从 716. 97 降低至 14. 27 nT, 三分量的均方根误差分别从 422. 86、240. 68、676. 21 nT 降低至 54. 21、52. 34、38. 61 nT,结果表明,该算法可显著提高航磁矢量的动态测量精度。

英文摘要:

The interference field caused by the airborne platform is one of the main sources of error in aeromagnetic measurement. In order to improve the accuracy of the aeromagnetic measurement of the geomagnetic vector, a vector aeromagnetic compensation algorithm based on component constraints is designed, and a compensation model including fixed, induced and eddy current magnetic interference is established. By introducing the attitude information of the carrier obtained by the inertial sensor, the problem of solving the compensation coefficient is linearized, and the parameter is solved by the least square method. The simulation results show that the algorithm can accurately estimate the compensation coefficient and reduce the root mean square error of the magnetic field vector to within 3 nT. The flight verification test was carried out using the helicopter aeromagnetic measurement system. After compensation, the root mean square error of the total field was reduced from 716. 97 to 14. 27 nT, and the root mean square error of the three components was reduced from 422. 86, 240. 68, and 676. 21 nT to 54. 21, 52. 34, 38. 61 nT, respectively. The results show that the algorithm can significantly improve the dynamic measurement accuracy of the aeromagnetic vector.

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