Uporaba variacij pospeška zaradi vpliva Lune in Sonca pri izračunu tirnic satelitov GLONASS

Implementation of the variation of the luni-solar acceleration into GLONASS orbit calculus

Author(s):

Sid Ahmed Medjahed, Abdelhalim Niati, Noureddine Kheloufi, Habib Taibi

Abstract:

In the differential equation system describes the motion of GLONASS satellites (rus. Globalnaya Navigazionnaya Sputnikovaya Sistema, or Global Navigation Satellite System ), the acceleration caused by the luni-solar traction is often taken as a constant during the period of the integration. In this work-study, we assume that the acceleration due to the luni-solar traction is not constant but varies linearly during the period of integration following this assumption; the linear functions in the three axes of the luni-solar acceleration are computed for an interval of 30 min and then implemented into the differential equations. The use of the numerical integration of Runge-Kutta fourth-order is recommended in the GLONASS-ICD (Interface Control Document) to solve for the differential equation system in order to get an orbit solution. The computation of the position and velocity of a GLONASS satellite in this study is performed by using the Runge-Kutta fourth-order method in forward and backward integration, with initial conditions provided in the broadcast ephemerides file.

Keywords:

luni-solar acceleration, satellite, ephemerides, Runge-Kutta method, forward integration, backward integration

DOI: 10.15292/geodetski-vestnik.2021.03.459-471

Citation:

Sid Ahmed Medjahed, Abdelhalim Niati, Noureddine Kheloufi, Habib Taibi (2021). Uporaba variacij pospeška zaradi vpliva Lune in Sonca pri izračunu tirnic satelitov GLONASS. | Implementation of the variation of the luni-solar acceleration into GLONASS orbit calculus. Geodetski vestnik, 65 (3), 459-471. DOI: 10.15292/geodetski-vestnik.2021.03.459-471