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Proceedings Paper

Trending of SNPP ephemeris and its implications on VIIRS geometric performance
Author(s): Guoqing (Gary) Lin; Robert E. Wolfe; James C. Tilton
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Paper Abstract

This paper describes trends in the Suomi National Polar‐orbiting Partnership (SNPP) spacecraft ephemeris data over the four and half years of on-orbit operations. It then discusses the implications of these trends on the geometric performance of the Visible Infrared Imaging Radiometer Suite (VIIRS), one of the instruments onboard SNPP. The SNPP ephemeris data includes time stamped spacecraft positions and velocities that are used to calculate the spacecraft altitude and sub-satellite locations. Through drag make-up maneuvers (DMUs) the orbital mean altitude (spacecraft altitude averaged over an orbit) has been maintained at 838.8 km to within +/- 0.2 km and the orbital period at 101.5 minutes to within +/- 0.2 seconds. The corresponding orbital mean velocity in the terrestrial frame of reference has been maintained at 7524 m/s to within +/- 0.5 m/s. Within an orbit, the altitude varies from 828 km near 15° N to 856 km near the South Pole. Inclination adjust maneuvers (IAMs) have maintained the orbit inclination angle at 98.67° to with +/- 0.07° and the sun-synchronous local time at ascending node (LTAN) at 13:28 to within +/- 5 minutes. Besides these trends, it is interesting to observe that the orbit’s elliptic shape has its major axis linking the perigee and apogee shorter than the line linking the ascending node and the descending node. This effect is caused by the Earth’s oblate spheroid shape and deviates from a Keplerian orbit theory in which the two orbiting bodies are point masses. VIIRS has 5 imagery resolution bands, 16 moderate resolution bands and a day-night band, with 32, 16 and 16 detectors, respectively, aligned in the spacecraft flight (aka. track) direction. For each band’s sample within a scan, the detectors sample the Earth’s surface simultaneously in the track direction in the Earth Centered Inertial frame of reference. The distance between the center of the area sensed by the trailing detectors of one scan and the leading detectors of the next includes a component caused by earth rotation. This earth rotation component is relatively small (~70 m/s) for an orbit like SNPP, but must be taken into account in the design of low-Earth orbit scanning sensors similar to VIIRS to ensure contiguous coverage at nadir.

Paper Details

Date Published: 5 October 2016
PDF: 11 pages
Proc. SPIE 9972, Earth Observing Systems XXI, 99721K (5 October 2016); doi: 10.1117/12.2239043
Show Author Affiliations
Guoqing (Gary) Lin, Science Systems and Applications Inc. (United States)
NASA Goddard Space Flight Ctr. (United States)
Robert E. Wolfe, NASA Goddard Space Flight Ctr. (United States)
James C. Tilton, NASA Goddard Space Flight Ctr. (United States)


Published in SPIE Proceedings Vol. 9972:
Earth Observing Systems XXI
James J. Butler; Xiaoxiong (Jack) Xiong; Xingfa Gu, Editor(s)

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