View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 41724U 16047A 25093.58950595 0.00000000 00000-0 00000-0 0 04
2 41724 3.1811 34.4151 0005050 211.9298 148.0506 1.00270000 08
| Epoch (UTC): | 03 April 2025 14:08:53 |
| Eccentricity: | 0.0005050 |
| inclination: | 3.1811° |
| perigee height: | 35765 km |
| apogee height: | 35808 km |
| right ascension of ascending node: | 34.4151° |
| argument of perigee: | 211.9298° |
| revolutions per day: | 1.00270000 |
| mean anomaly at epoch: | 148.0506° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|