A new method for calculating a satellite trajectory with a view to tracking automatization
Abstract
The paper describes a new method for calculating satellite ephemerides above a station. Applicable to any satellite system, it is particularly suitable to laser rangefinding stations. It is based on the 'two-centers' and the perturbed Keplerian dynamics, and its principle can be summarized as follows. Knowing the six osculating parameters of the orbit at initial time, one calculates the satellite ephemerides at a subsequent time by assimilating its orbit between the initial time and the time in question to a Keplerian motion about a fictitious gravitation center. For a passage of some 20 minutes this method, which uses only a single set of osculating parameters, ensures a precision of 100 to 200 meters of distance and 0.01 degree on angles as compared with a complete prediction calculation.
- Publication:
-
NASA STI/Recon Technical Report A
- Pub Date:
- 1975
- Bibcode:
- 1975STIA...7614459S
- Keywords:
-
- Ephemerides;
- Orbit Calculation;
- Satellite Orbits;
- Satellite Tracking;
- Automatic Control;
- Double Cusps;
- Kepler Laws;
- Laser Range Finders;
- Orbit Perturbation;
- Astrodynamics