View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 39153U 26106.41094125 +.00000000 +00000-0 +11196-3 0 00006
2 39153 98.1593 263.6432 0011588 357.9192 2.1978 14.96914006 00
| Epoch (UTC): | 16 April 2026 09:51:45 |
| Eccentricity: | 0.0011588 |
| inclination: | 98.1593° |
| perigee height: | 568 km |
| apogee height: | 584 km |
| right ascension of ascending node: | 263.6432° |
| argument of perigee: | 357.9192° |
| revolutions per day: | 14.96914006 |
| mean anomaly at epoch: | 2.1978° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|