An Image Compensation Method for the Camera Onboard SDLT-1 Satellite of China

For geostationary satellite, small motion of the satellite platform will tremendously deviate the line of sight (LOS) of the imager and an image compensation method (ICM) is needed to ensure the accuracy of the image navigation and registration (INR) of such satellite. Some geostationary satellites...

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Bibliographic Details
Published in:Journal of the Indian Society of Remote Sensing 2022-09, Vol.50 (9), p.1641-1650
Main Authors: Huang, Jie, Xi, Juntong
Format: Article
Language:English
Subjects:
Compensation
Deformation
Detectors
Earth and Environmental Science
Earth Sciences
Feasibility
Line of sight
Pixels
Remote Sensing/Photogrammetry
Research Article
Satellite imagery
Satellite tracking
Satellites
Space debris mitigation
Synchronous satellites
Three axis
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Summary:For geostationary satellite, small motion of the satellite platform will tremendously deviate the line of sight (LOS) of the imager and an image compensation method (ICM) is needed to ensure the accuracy of the image navigation and registration (INR) of such satellite. Some geostationary satellites share the same characteristic that the detectors are all small (FY-4 has 16 pixels in line), which make it possible to represent the LOS vector of each pixel by the LOS vector of the center pixel. In such a situation, it is a feasible way to apply the compensation factors to the control loops of the SRM to achieve an accurate image compensation result. The image detector onboard the satellite is a 10,240 by 10,240 pixels array which makes the traditional image compensation method used for small size detectors infeasible. In such a situation, an image compensation method (ICM) is proposed for the geostationary space debris locating and tracking (SDLT-1) satellite of China. To testify the feasibility of the proposed method, an experiment based on three-axis air-bearing physical simulator equipment is designed and the results show that the fluctuation of both the EW deformation and NS deformation is tremendously restrained below 18urad from 175urad which is applicable for on-orbit mission.
ISSN:0255-660X
0974-3006
DOI:10.1007/s12524-022-01555-2