View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 04138U 26088.18186279 +.00000000 +00000-0 +23039-4 0 00006
2 04138 74.0415 20.8018 0011969 41.1981 319.0079 14.46463413 03
| Epoch (UTC): | 29 March 2026 04:21:52 |
| Eccentricity: | 0.0011969 |
| inclination: | 74.0415° |
| perigee height: | 729 km |
| apogee height: | 746 km |
| right ascension of ascending node: | 20.8018° |
| argument of perigee: | 41.1981° |
| revolutions per day: | 14.46463413 |
| mean anomaly at epoch: | 319.0079° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|