View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 20624U 26037.56120759 +.00000000 +00000-0 -63594-4 0 00002
2 20624 71.0397 85.9221 0017338 254.7185 105.2021 14.14825817 06
| Epoch (UTC): | 06 February 2026 13:28:08 |
| Eccentricity: | 0.0017338 |
| inclination: | 71.0397° |
| perigee height: | 830 km |
| apogee height: | 855 km |
| right ascension of ascending node: | 85.9221° |
| argument of perigee: | 254.7185° |
| revolutions per day: | 14.14825817 |
| mean anomaly at epoch: | 105.2021° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|