View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 20150U 26020.80404691 +.00000000 +00000-0 +87824-4 0 00006
2 20150 82.9412 284.8088 0029277 151.8353 268.6929 13.75900310 08
| Epoch (UTC): | 20 January 2026 19:17:49 |
| Eccentricity: | 0.0029277 |
| inclination: | 82.9412° |
| perigee height: | 957 km |
| apogee height: | 1000 km |
| right ascension of ascending node: | 284.8088° |
| argument of perigee: | 151.8353° |
| revolutions per day: | 13.75900310 |
| mean anomaly at epoch: | 268.6929° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|