Abstract

Aeromagnetic surveys play an important role in many fields, for example, archaeology, anti-submarine warfare, and geophysical exploration. Being in the geomagnetic field, the aircraft generates a great deal of magnetic interference, resulting in bad performance during detection surveys. Thus, it is necessary and important to perform aeromagnetic compensation in advance. Conventional aeromagnetic compensation methods consider that the geomagnetic gradient is approximately zero after bandpass filtering, bringing about the inaccuracy of compensation coefficients. To address this issue, an improved aeromagnetic compensation method robust to geomagnetic gradient is proposed. In this study, the International Geomagnetic Reference Field (IGRF) model was employed to model the geomagnetic gradient. Then, the estimated geomagnetic gradient was subtracted from the measured data, which improved the accuracy of the compensation equations. Field experiments were conducted to verify the effectiveness of the proposed method. The experimental results show that compared to the traditional method, the compensation performance of the proposed method was improved by 152% to 329%. For the level flight, the standard deviation of residual noise after compensation can be as low as 3.3pT. The results indicate that the proposed method can significantly improve the compensation effect, showing great benefits for weak magnetic anomaly detection.

Highlights

  • Pumped magnetometer data and three-axis magnetometer data were recorded on the rising edge of the pulse per second (PPS), which was obtained data were recorded the rising of the pulse per second (PPS), which was to obtained from the DGPS

  • The traditional aeromagnetic compensation method does not take into consideration The traditional aeromagnetic compensation method does not take into consideration the influence of the geomagnetic gradient

  • The interference field obtained after bandpass the influence of the geomagnetic gradient

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Summary

Tolles–Lawson Model

To compensate for the platform-generated interference field, a three-axis fluxgate. 2.1. The eddy current, generated by the maneuvers thethe metal components of the aircraft, where ci (i = 4, ..., 9) is the compensation coefficientofof induced magnetic field, and is proportional to the time change rate of the flux through these components. HEDDY (t)bycan expressed of as follows: The interference eddy current, generated thebemaneuvers the metal components of the aircraft, is proportional to the time change rate of the flux through these components. 0 (i = 1, 2, 3), and the magnitude of the geomagnetic field It can be clearly derivatives u demonstrated i that the interference field generated by the platform would be well elimidemonstrated that the compensation interference field generatedcan by the platform would be well eliminated nated if the accurate coefficients be obtained.

Calibration Flight
Proposed Aeromagnetic
By deriving the scalar potential radial component
Aeromagnetic Survey System
Methods
Data Analysis
Table At
Method
Conclusions
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