View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 29050U 26106.26353773 +.00000000 +00000-0 +17741-3 0 00003
2 29050 72.0117 86.4580 0041983 37.1002 323.3043 14.66798635 08
| Epoch (UTC): | 16 April 2026 06:19:29 |
| Eccentricity: | 0.0041983 |
| inclination: | 72.0117° |
| perigee height: | 642 km |
| apogee height: | 701 km |
| right ascension of ascending node: | 86.4580° |
| argument of perigee: | 37.1002° |
| revolutions per day: | 14.66798635 |
| mean anomaly at epoch: | 323.3043° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|