Magnetic interference testing method for an electric fixed-wing unmanned aircraft system (UAS)-Reference-Cited by-同舟云学术

Magnetic interference testing method for an electric fixed-wing unmanned aircraft system (UAS)

Published:2018-09-01 Issue:3 Volume:6 Page:177-194
ISSN:2291-3467
Container-title:Journal of Unmanned Vehicle Systems
language:en
Short-container-title:J. Unmanned Veh. Sys.

Author:

Tuck L.¹,Samson C.¹²,Laliberté J.³,Wells M.⁴,Bélanger F.⁴

Affiliation:

1. Department of Earth Sciences, Carleton University, 1125 Colonel By Drive, Ottawa, ON K1S 5B6, Canada.

2. Department of Construction Engineering, École de Technologie Supérieure, 1100 Notre-Dame Ouest, Montréal, QC H3C 1K3, Canada.

3. Department of Mechanical and Aerospace Engineering, Carleton University, Ottawa, ON K1S 5B6, Canada.

4. Sander Geophysics Ltd., 260 Hunt Club Road, Ottawa, ON K1V 1C1, Canada.

Abstract

One of the barriers preventing unmanned aircraft systems (UASs) from having a larger presence in the geophysical magnetic surveying industry is the magnetic interference generated by the UAS and its impact on the quality of the recorded data. Detailed characterization of interference effects is therefore needed before remedial solutions can be proposed. A method for characterizing magnetic interference is demonstrated for a 21 kg, 3.7 m wingspan, 6 kW electric fixed-wing UAS purposely built for magnetic surveying. It involves mapping the spatial variations of the total magnetic intensity resulting from the interference sources on the UAS. Dynamic tests showed that the motor should be engaged and the aircraft control surfaces levelled prior to mapping. Experimental results reveal that the two strongest sources of magnetic interference are the cables connecting the motor to the batteries, and the servos. Combining three factors to assess the level of magnetic interference — the total magnetic intensity, 4th difference and vertical magnetic gradient — an index overlay shows that the magnetic sensor(s) should be located at least 50 cm away from the wingtips or tail to ensure an interference level of <2 nT, a 4th difference of <0.05 nT, and a gradient of <10 nT/m.

Publisher

Canadian Science Publishing

Subject

Electrical and Electronic Engineering,Control and Optimization,Computer Science Applications,Aerospace Engineering,Automotive Engineering,Control and Systems Engineering

Link

http://www.nrcresearchpress.com/doi/pdf/10.1139/juvs-2018-0006

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