View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 25542U 26159.42585750 +.00000000 +00000-0 -29400-3 0 00009
2 25542 6.5742 187.9209 7137440 149.5213 285.4162 2.33854508 07
| Epoch (UTC): | 08 June 2026 10:13:14 |
| Eccentricity: | 0.7137440 |
| inclination: | 6.5742° |
| perigee height: | 485 km |
| apogee height: | 34710 km |
| right ascension of ascending node: | 187.9209° |
| argument of perigee: | 149.5213° |
| revolutions per day: | 2.33854508 |
| mean anomaly at epoch: | 285.4162° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|