View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 58902U 26145.11187187 +.00000000 +00000-0 +11818-2 0 00000
2 58902 97.3874 8.2552 0005250 163.0940 197.0509 15.90640870 02
| Epoch (UTC): | 25 May 2026 02:41:05 |
| Eccentricity: | 0.0005250 |
| inclination: | 97.3874° |
| perigee height: | 297 km |
| apogee height: | 304 km |
| right ascension of ascending node: | 8.2552° |
| argument of perigee: | 163.0940° |
| revolutions per day: | 15.90640870 |
| mean anomaly at epoch: | 197.0509° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|