Implementation of the variation of the luni-solar acceleration into GLONASS orbit calculus
| Autor: | Noureddine Kheloufi, Abdelhalim Niati, Habib Taibi, Sid Ahmed Medjahed |
|---|---|
| Jazyk: | angličtina |
| Rok vydání: | 2021 |
| Předmět: |
Physics
QB275-343 satellite medicine.disease backward integration Computational physics luni-solar acceleration Acceleration medicine runge-kutta method General Earth and Planetary Sciences GLONASS Orbit (control theory) Variation (astronomy) ephemerides forward integration Calculus (medicine) Geodesy |
| Zdroj: | Geodetski Vestnik, Vol 65, Iss 03, Pp 459-471 (2021) |
| ISSN: | 1581-1328 0351-0271 |
| Popis: | 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. |
| Databáze: | OpenAIRE |
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