View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 04256U 26112.26091198 +.00000000 +00000-0 +79668-4 0 00008
2 04256 70.0081 85.1556 0017867 145.4862 214.7410 13.99181109 05
| Epoch (UTC): | 22 April 2026 06:15:42 |
| Eccentricity: | 0.0017867 |
| inclination: | 70.0081° |
| perigee height: | 884 km |
| apogee height: | 910 km |
| right ascension of ascending node: | 85.1556° |
| argument of perigee: | 145.4862° |
| revolutions per day: | 13.99181109 |
| mean anomaly at epoch: | 214.7410° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|