IRNSS is one of the unique constellations first of its type dedicated for providing the satellite-based navigation in Indian subcontinent. The IRNSS constellation consists of seven satellites with three satellites in GEO orbit with inclination of 5° and four satellites in GSO orbits with inclination of 29°. The constellation is designed to get better satellite geometry in terms of Dilution of precision (DOP) over Indian region and its extended area. All satellites in the constellation provide 24 h visibility within and across geographic boundaries of Indian land mass with minimum elevation greater than 15°. This paper presents the variations of Keplerian elements of all four operational satellites of IRNSS Constellation. The satellite state vector, satellite clock and receiver clock parameters are estimated using consolidated orbit determination algorithm of Navigation software installed at ISRO Navigation Center. The estimated state vectors are converted into the Keplerian elements. The variations in the Keplerian elements show the expected behaviour showing the influences of natural perturbations like J2 effect, luni-solar perturbations, etc.
Orbital Parameters Variations of IRNSS Satellites
Lect.Notes Mechanical Engineering
Innovative Design and Development Practices in Aerospace and Automotive Engineering ; Kapitel : 57 ; 537-548
2016-09-18
12 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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