航空磁通门全张量仪校正及磁补偿方法研究

发布时间：2017-12-28 13:14

本文关键词：航空磁通门全张量仪校正及磁补偿方法研究　出处：《吉林大学》2017年硕士论文　论文类型：学位论文

【摘要】：磁梯度张量仪是一种测量磁场空间变化率的仪器,可以被装载到飞行平台中进行航空地球物理探测,具有空间分辨率高、信息丰富等特点,特别适合发现浅层隐伏矿、磁性运动目标等。磁梯度张量仪一般是由可以测量磁矢量的传感器如超导和磁通门等,按一定空间分布来构成。使用磁通门作为核心组件设计的磁梯度张量仪具有适用温度范围广,成本低和高分辨率的优点。然而,有两个关键问题大大降低了磁通门全张量仪的数据质量:一是磁通门全张量仪存在多种系统误差,比如标度因子误差、非正交误差、零偏误差、动态误差、非线性误差以及由安装造成的非对准误差;另一个是如果磁通门全张量仪和飞行器安装距离非常近,飞行器在地磁场中的飞行会对磁通门全张量仪产生电磁干扰,比如硬磁干扰、软磁干扰以及涡流磁干扰。当磁通门全张量仪距离飞行器非常远时,其采集到的数据只受自身系统误差影响。针对这种应用情况,本文首先提出了一种基于不变量的磁通门全张量仪系统误差校正方法。该种方法首先建立单个磁通门误差校正模型,然后利用递推方法推导出磁通门全张量仪系统误差校正模型,最后两步完成磁通门全张量仪系统误差模型参数辨识:第一步先借助地磁场梯度在高空中接近为0的特性完成高空校正,第二步利用地面上非均匀磁场区域磁梯度张量不变量的旋转不变特性实现磁梯度张量分量之间的标度因子校正。本文以磁偶极子模型为基础进行了大量仿真实验,同时也开展了相应的野外实验。实验室仿真实验和野外直升机挂载“十字型”磁通门全张量仪的飞行实验都验证了该方法的有效性。野外实验区域内校正后磁梯度张量分量的RMS达到1n T/m,改善比范围从359.6到1765。考虑到当磁通门全张量仪和飞行器距离特别近时飞行器会产生磁干扰的情况,本文提出了一种磁通门全张量仪的系统误差校正及磁干扰补偿融合方法。该方法首先融合磁干扰模型和单个磁通门误差模型,然后利用递推的方法推导出磁梯度张量分量的校正及磁补偿模型,最后再利用高海拔地区磁梯度接近为0的特性得到校正及磁补偿系数。通过实验室仿真实验和野外滑翔翼装载“十字型”磁通门全张量仪的飞行实验评估了该方法的性能。野外实验区域内校正后磁梯度张量分量的RMS达到2n T/m,改善比范围从4087.4到17526。本文提出的这两种方法非常容易扩展到其他结构的磁通门全张量仪和SQUID磁梯度张量仪。
[Abstract]:Magnetic gradiometer is a kind of instrument for measuring the rate of magnetic field spatial change. It can be loaded into the flight platform for aeronautical geophysical exploration, and has the characteristics of high spatial resolution and abundant information. It is especially suitable for finding shallow concealed ores and magnetic moving targets. Magnetic gradient tensor is usually made up of a sensor that can measure the magnetic vector, such as superconductivity and magnetic flux gate, according to a certain spatial distribution. Magnetic gradient tensor, which is designed by magnetic flux gate as core component, has the advantages of wide range of temperature, low cost and high resolution. However, there are two key problems greatly reduces the data quality of fluxgate instrument: a full tensor fluxgate full tensor instrument there are many systematic errors, such as scale factor error, non orthogonal error, bias error and dynamic error, nonlinear error and non alignment error caused by the installation; the other one is if fluxgate instrument and full tensor aircraft mounted very close distance, the aircraft in flight in the earth's magnetic field will produce electromagnetic interference on the fluxgate tensor instrument, such as magnetic interference, soft magnetic interference and eddy current magnetic interference. When the fluxgate total tensor is very far away from the aircraft, the data collected is only influenced by its own system error. In view of this application, this paper first proposes an error correction method based on the invariants for the fluxgate full tensor system. This method firstly establishes the fluxgate error correction model, and then use the recursive method to derive the full tensor fluxgate instrument system error correction model, the last two steps to complete the fluxgate full tensor for system error model parameter identification: in the first step with gradient magnetic field in the air close to 0 of the characteristics of complete altitude correction, second the homogeneous magnetic field of magnetic gradient tensor invariant rotation invariant features the scaling factor between the components of the magnetic gradient tensor correction of non ground. In this paper, a large number of simulation experiments have been carried out on the basis of the magnetic dipole model, and the corresponding field experiments are also carried out. The effectiveness of the method is verified by the laboratory simulation experiment and the flight experiment of the field helicopter mounted "cross type" fluxgate full tensor. The RMS of the corrected magnetic gradient tensor component in the field experiment area is 1n T/m, and the improvement range is from 359.6 to 1765. Considering that when the fluxgate tensor and the distance between aircraft are very close, the aircraft will generate magnetic interference. In this paper, a new method of correcting the system error and magnetic interference compensation of fluxgate tensor is proposed. First, the magnetic interference model and the single flux gate error model are fused. Then the correction and magnetic compensation model of magnetic gradient tensor components is deduced by recursive method. Finally, the correction coefficient and magnetic compensation coefficient are obtained by using the magnetic gradient approaching 0 in high altitude area. The performance of the method is evaluated by the laboratory simulation experiment and the flight experiment of the "cross type" fluxgate full tensor with the field glider. The RMS of the corrected magnetic gradient tensor component in the field experiment area is 2n T/m, and the improvement range is from 4087.4 to 17526. The two methods proposed in this paper are easily extended to other structures with fluxgate full tensor and SQUID magnetic gradient tensor.
【学位授予单位】：吉林大学
【学位级别】：硕士
【学位授予年份】：2017
【分类号】：P631.222

【相似文献】