View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 20625U 26020.76807441 +.00000000 +00000-0 -29627-4 0 00006
2 20625 70.9996 38.5562 0013795 6.7537 353.3769 14.15008008 02
| Epoch (UTC): | 20 January 2026 18:26:01 |
| Eccentricity: | 0.0013795 |
| inclination: | 70.9996° |
| perigee height: | 832 km |
| apogee height: | 852 km |
| right ascension of ascending node: | 38.5562° |
| argument of perigee: | 6.7537° |
| revolutions per day: | 14.15008008 |
| mean anomaly at epoch: | 353.3769° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|