View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 40614U 15022B 25359.93496764 0.00000000 00000-0 00000-0 0 00
2 40614 0.0160 108.2839 0003453 352.8976 7.0980 1.00270000 04
| Epoch (UTC): | 25 December 2025 22:26:21 |
| Eccentricity: | 0.0003453 |
| inclination: | 0.0160° |
| perigee height: | 35772 km |
| apogee height: | 35801 km |
| right ascension of ascending node: | 108.2839° |
| argument of perigee: | 352.8976° |
| revolutions per day: | 1.00270000 |
| mean anomaly at epoch: | 7.0980° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|