Abstract
Super low altitude remote sensing satellites maintain lower flight altitudes by means of ion propulsion in order to improve image resolution and positioning accuracy. The use of engineering data in design for achieving image positioning accuracy is discussed in this paper based on the principles of the photogrammetry theory. The exact line-of-sight rebuilding of each detection element and this direction precisely intersecting with the Earth's elliptical when the camera on the satellite is imaging are both ensured by the combined design of key parameters. These parameters include: orbit determination accuracy, attitude determination accuracy, camera exposure time, accurately synchronizing the reception of ephemeris with attitude data, geometric calibration and precise orbit verification. Precise simulation calculations show that image positioning accuracy of super low altitude remote sensing satellites is not obviously improved. The attitude determination error of a satellite still restricts its positioning accuracy.
Highlights
Remote sensing of the Earth by observation satellite systems has been an important means of obtaining information of our aerospace
For a long time the geometric correction of remote sensing images has required sufficient uniformly distributed Ground Control Points (GCP). This is dependent on extrapolating the parameters of the satellite and a crucial task for the geometric correction of an image is to calculate the image position accuracy of the GCPs
SPOT‐ 5 [1], IKONOS [2], QuickBird [3] and ALOS [4] are some of the current commercial international high resolution remote sensing satellites
Summary
Remote sensing of the Earth by observation satellite systems has been an important means of obtaining information of our aerospace. Solar electric propulsion technology has been approaching perfection since the first GOCE satellite was launched in 2009 This satellite is kept in a lower orbit to improve remote sensing image quality. This paper uses engineering data on the imaging positioning accuracy of satellites combined with the system design program of super low orbit remote sensing satellites. The exact line‐of‐sight rebuilding of each detection element and this direction precisely intersecting with the Earth’s elliptical when the camera on the satellite is imaging, are ensured by the joint design of key parameters These parameters include: orbit determination accuracy, attitude determination accuracy, camera exposure time, accurately synchronizing the reception of ephemeris with attitude data, geometric calibration and precise orbit verification. Z ZS where [XS, YS, ZS]T is the location of the satellite in a WGS‐ 84 coordinate system during imaging, is the imaging scale, [X, Y, Z]T is the position of intersection with M
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