Open AccessImplementation of the variation of the luni-solar acceleration into GLONASS orbit calculus
Author(s) -
Sid Ahmed Medjahed,
Abdelhalim Niati,
Noureddine Kheloufi,
Habib Taibi
Publication year - 2021
Publication title -
geodetski vestnik
Language(s) - English
Resource type - Journals
eISSN - 1581-1328
pISSN - 0351-0271
DOI - 10.15292/geodetski-vestnik.2021.03.459-471
Subject(s) - geodesy , glonass , acceleration , satellite , orbit (dynamics) , path integration , numerical integration , runge–kutta methods , physics , ephemeris , differential equation , mathematics , computer science , mathematical analysis , geography , aerospace engineering , engineering , classical mechanics , astronomy , gnss applications , artificial intelligence
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.